Embry ASCI310 Full Course latest
Embry ASCI310 Full Course latest
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Embry ASCI310 Module 1.6 Discussion
1.6 - DQ: Physical Laws
62 62 unread replies. 84 84 replies.
Discussion Item
Within the context of Newton's three laws of motion, compare and contrast the motions of an apple falling off a tree to an airplane taking off.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Evaluation
Each graded discussion will be evaluated according to the attached rubric. This message will not be repeated. Please read these instructions for information on accessing the discussion rubric. (Links to an external site.)
Embry ASCI310 Module 2.5 Discussion latest 2016 December
2.5 - DQ: Atmospheric Properties and Airspeed Measurement
7070 unread replies.8181 replies.
Discussion Item
• After reading archived FAA Circular 91.XX and the Flight Safety Digest article on RVSM, comment on the significant hurdles to accurately display and accurately fly an assigned altitude.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 3.4 Discussion latest 2016 December
3.4 - DQ: Lift and Drag
7979 unread replies.9090 replies.
Discussion
• According to the Boeing Aero Magazine article on Angle of Attack (AOA), when is AOA good to use in commercial airliners? How is it useful in Military fighter jets? Comment on how you have used AOA in your own flying.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 4.6 Discussion latest 2016 December
4.6 - DQ: Engine Thrust
6969 unread replies.7676 replies.
Discussion Items
1. Compare and contrast engine specifications, including thrust, weight, and bypass ratios for the GE F404 and J85; two very common engines. What aircraft use these engines? List your source.
2. Compare and contrast the largest turbo engine to the smallest turbo engine. List your source.
3. Compare and contrast the largest turbo propeller engine to the largest reciprocating propeller engine? List your source.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 5.4 Discussion latest 2016 December
5.4 - DQ: Weight and Balance
7575 unread replies.8484 replies.
Discussion Items
1. Where is the aircraft aerodynamic center typically located during subsonic flight and what happens if the CG is behind the aircraft's aerodynamic center?
2. What is the danger of calculating the Weight and Balance and determining that the CG is forward of the limit ? What can you do as Loadmaster or Pilot in Command to deal with this condition?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 6.5 Discussion latest 2016 December
6.5 - DQ: Takeoff and Landing
7272 unread replies.8383 replies.
Discussion Items
1. After reading this week's additional literature on takeoffs and landings, post one paragraph on your impressions, comments, or lessons learned from the readings.
2. Imagine you are the captain of a transport airplane and your balanced field length or critical field length is longer than the runway available. What should you do? What are your available options?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 7.5 Discussion latest 2016 December
7.5 - DQ: Climb and Descent
7474 unread replies.8585 replies.
Discussion Items
1. How does VOPT (Optimum Climb speed) compare to VY (Max Rate of Climb)? Most transport airplane climb schedules are based on what type profile and why?
2. What chain of events led to the Gimli Glider Incident? What were the factors that saved the airplane and passengers?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 8.3 Discussion latest 2016 December
8.3 - DQ: Range and Endurance
5151 unread replies.6565 replies.
Discussion Item
• Imagine you are flying your jet glider around the world. How can you optimize range performance in the planning and flying stages?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 9.2 Discussion latest 2016 December
9.2 - DQ: Aircraft Performance Experiences
5555 unread replies.7575 replies.
Discussion Items
1. What interesting aircraft performance stories have you experienced, heard, or read about happening at Denver International Airport (KDEN) or Chicago O'Hare International Airport (KORD)?
2. What factors from such experiences can you relate to what you have learned from completing your Aircraft Performance Project?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 1 Assignment Exercise 1 latest 2016 December
Exercise 1: Rectilinear Motion
Background
The average accelerations of a US Navy fighter jet takeoff to an US Air Force fighter jet takeoff are very different. The aircraft conditions are the same except the Air Force fighter is on a 12,000-ft dry concrete runway and the Navy fighter is on the catapult of an aircraft carrier. (Hint: You will have to use two different methods because you are not given the catapult force, but you have the catapult distance. Assume aircraft is airborne after the catapult stroke.)
Givens:
Gross Weight (W) = 55,000 lb
Average Drag (D) = 9,000 lb
Average Friction (f) = 1,500 lb
Average Thrust (T) = 36,000 lb
Lift Off Speed ( VLO) 180 KTAS
Catapult Distance = 350 ft
1. Compute the average acceleration of the Air Force Fighter during the takeoff roll (ft/s 2).
2. What would be the length of the takeoff roll for the Air Force Fighter (ft)?
3. How long (time) would it take for the Air Force Fighter to liftoff (sec)?
4. Compute the average acceleration of the Navy Fighter during catapult launch (ft/s2).
5. How long (time in seconds) does it take for the Navy fighter to takeoff with a catapult launch?
6. Find potential, kinetic, and total energy of this aircraft after takeoff at the following conditions:
Weight = 50,000 lb
Altitude = 10,000 ft
Airspeed = 300 KTAS
7. Given conditions of #6, find new altitude if the aircraft raises the nose to capture 250 KTAS but keeps the thrust at the same setting and, for simplicity, assume the drag stays the same. Think of this as a Constant Energy Problem.
8. Find Energy Height (TE/W) of aircraft at 300 KTAS and 10,000 ft.
Embry ASCI310 Module 2.6 Assignment Exercise 2 latest 2016 December
Exercise 2: Airspeed Determination
Givens:
Altitude: FL310 (31,000 ft Pressure Altitude)
Indicated Airspeed: 250 KIAS
Indicated Outside Air Temperature (IOAT) or Total Temperature: -30 deg C
Figure 2.1 for Atmosphere
Figure 3.1 Position Errors
Figure 3.2 Compressibility Errors
Figure 11.2 or Tt= Ta(1 + .2M2) Temperature Ram Rise
1. Find CAS (Calibrated Airspeed in kts).
2. Find EAS (Equivalent Airspeed in kts).
3. Find Pressure Ratio: .
4. Find Mach.
5. Find Actual Outside Air Temperature (ambient temperature).
6. Find Temperature Ram Rise.
7. Find Density Ratio: .
8. Find TAS, True Airspeed in kts.
9. If you are landing into an airfield in mountainous terrain at afield elevation of 3,000 ftMSL (Mean Sea Level) and the field outside air temperature is -24 deg C, according to AC 91-XX Draft Appendix 2, how should you adjust your approach arrival procedures with a Final Approach Fix (FAF) at 5,000 ftMSL and your Minimum Descent Altitude (MDA) at 3500 ftMSL?
Embry ASCI310 Module 4.7 Assignment Exercise 4 latest 2016 December
Exercise 4: Thrust Available
Given Aircraft Conditions:
Gross Weight for Cruise = 300,000 lbs
Wing Area = 3050 ft2
Wing Span = 156 ft
Wing Efficiency = .80
CDp= 0.0119
Twin turbofan engine Aircraft
Thrust @ sea level = 50,000 lb/per engine
Temp-Standard
Figure 2.1
Figures 4.3 and 4.5
Figure 5.1
Figure 6.5
1. Using Figure 6.5, find Thrust Available at 100 % RPM Max Endurance Airspeed at FL350 (Both Engines). Does the Thrust Available exceed the thrust required from Exercise 3?
2. Using Figure 6.5 (Equation 6.2), find the Total Fuel Flow (both engines) to maintain Max endurance speed in Level flight at FL350?
3. What would the % thrust and % N1setting be at Max Endurance Speed, FL350? Assume Thrust available from Problem 1,Thrust Required from Exercise 3, andin Equation 6.4 use 5.0 for x for turbofan engines.
4. UsingFigure 6.5, if you lost one engine, would you be able to maintain level flight at Max Endurance Airspeed at FL250?
5. How would the Altitude (FL350 as compared to FL250) affect the Induced and Parasite drag on the aircraft atconstant true airspeed?
Embry ASCI310 Module 5.5 Assignment Exercise 5 latest 2016 December
Exercise 5: Weight and Balance
Use the aircraft specifications given below to answer the questions:
Basic operating weight 90,000 lb
Maximum zero fuel weight 120,000 lb
Maximum landing weight 140,000 lb
Maximum takeoff weight 170,000 lb
Fuel tank load 25,000 lb
Estimated fuel burn en route 15,000 lb
Field limited weight 160,000 lb
Obstacle limited weight 150,000 lb
Total Moment (takeoff) 92,437,500 lb-in.
LEMAC 600 in.
TEMAC 750 in.
Forward Cargo Station 200 in.
Aft Cargo Station 700 in.
1. What is the maximum allowable payload for this flight?
2. Assuming the aircraft is loaded with maximum allowable payload, what is the takeoff CG (inches)?
3. Assuming the aircraft is loaded with maximum allowable payload, what is the takeoff CG (percent MAC)?
4.Suppose we need to shift the CG to 20% MAC. How much weight should be moved from the aft cargo hold to the forward cargo hold?
Embry ASCI310 Module 6.6 Assignment Exercise 6 latest 2016 December
Exercise 6: Takeoff and Landing Performance
Given Conditions:
Weight 300,000 lb
Density Altitude 5,000 ft
Temperature Standard
Configuration Flaps-5
V speeds Figure 9.19
No Wind/No Slope
Thrust 103% Full
Takeoff ground roll distance 4000 ft
Balance Field Length (BFL) 7500 ft
1. Find V1, V2, VR(see Figure 9.19).
2. For a new weight of 350,000 lb and using Table 7.2 Summary of Useful Takeoff Proportions in Modern Jet Transportation Performance, find the following:
a) Takeoff Ground Roll with weight increased to 350,000 lb.
b) VR(assume Rotation Speed is solely a function of stall speed).
3. For a new weight of 300,000 lb, sea level Density Altitude,and using Table 7.2 in the Lewis textbook, find the Takeoff Ground Roll.
4. For a new weight of weight 300,000, increased wind to 20 kts of headwind, and Density Altitude of 5,000 ft, find the Takeoff Ground Roll.
5. How does an increase in Density Altitudeaffect V1, V2, VR, BFL?
6. How does an increase in Weight affect V1, V2, VR, andBFL?
7. How does a slippery runway affect V1, V2, VR, and BFL?
8. If you increase the takeoff weight by 10% (i.e., 300,000lb to 330,000 lb), what is the rule of thumb increase in takeoff distance and rotation speed in percentage?
9. If an aircraft is able to climb 35 ft after 1000 ft of horizontal travel on takeoff, what is the climb gradient (%) and climb angle (deg)?
Embry ASCI310 Module 7.6 Assignment Exercise 7 latest 2016 December
Exercise 7: Climb
1. Given conditions of “Saw-tooth” climb flight test.
Pressure Altitude-2000 ft Weight 300,000 lbs
Single engine Method Constant Airspeed Climb +/- 500 ft
Temperature:Standard (Climb from 1500 ft to 2500 ft)
Assume negligible airspeed errors due to position and compressibility
Airspeed Airspeed Climb Time Average Rate of Climb Average Rate of Climb Angle of Climb
(KIAS) (KTAS) (s) (ft/min) (kts) (deg)
140 80
160 65
180 60
190 70
Fill out the above table.
Find: (a) Indicated Airspeed for Vx(Best Angle Climb Airspeed) and Vy(Best Rate of Climb Airspeed)
(b) Angle of Climb for Vx
(c) Rate of Climb for Vy
(d) Specific Excess Power at Vy
(e) Excess Thrust at Vy and Vx
2. Follow on from Exercise 4:
Given Conditions:
Gross Weight for Cruise = 300,000 lbs
Wing Area = 3050 ft2
Wing Span = 156 ft
Wing Efficiency = .80
CDp= 0.0119
Twin turbofan engine Aircraft
Thrust @ sea level = 50,000 lb/per engine
Temp-Standard
Figure 2.1
Figure 4.3, 4.5
Figure 5.1
Figure 6.5
(a) Find Rate of Climb at Max Endurance Airspeed at FL350 100% RPM (Thrust Available from Exercise 4 and Thrust Required from Exercise 3).
(b) Find Angle of Climb at Max Endurance Airspeed at FL350 100% RPM (Thrust Available from Exercise 4 and Thrust Required from Exercise 3).
3. Find Cost Index (lb/hr) of an aircraft that has operating costs including maintenance and aircrew of $ 3,000 /hr with fuel costs of $5.00 / gallon.
Assume Jet Fuel = 6.8lb/gallon.
Embry ASCI310 Module 8.4 Assignment Exercise 8 latest 2016 December
Exercise 8: Range/Endurance
Givens Conditions:
Gross Weight for Beginning of Cruise = 300,000 lbs
Gross Weight at End of Cruise = 200,000 lbs
Altitude = FL350
Standard Conditions
Wing Area = 3050 ft2
Wing Span = 156 ft
Wing Efficiency = .75
CDp= 0.0119
Twin turbofan engines
Figure 2.1
Figure 6.5
Figure 13.2
No need to take into account Temperature Ram Rise
1. Find Equivalent Airspeed, True Airspeed, and Mach for best range at FL350 and Sea Level at W=300,000 lb. (Use Figure 13.2 and Equations 4.6, 3.8. and 3.4.)
2. Assuming constant altitude,find the best Range Equivalent Airspeed, True Airspeed, and Mach at the end of cruise for W=200,000 lb at FL350, and Sea Level. (Use Figure 13.2 and Equations 4.6, 3.8, and 3.4.)
3. Find Range (nm)at Sea Level and at constant FL350.Assume altitude remains constant, AOA remains constant, and Airspeed varies (Use Equation 13.1.)
4. Compare specific ranges at FL350 W = 300,000 lb and W = 200,000 lb. (Use Equation 12.2.)
5. Find Equivalent Airspeed, True Airspeed, and Mach for best endurance at FL350 and Sea Level at W= 300,000 lb.
6. Assuming Constant Altitude, what is best Endurance Equivalent Airspeed, True Airspeed, and Mach at W=200,000 lb?
7. Find Best Endurance (hours)at FL350 (use Equation 13.9) using the same gross weight differences.
8. How much does it cost a B-737 to carry an extra 10,000 lb of fuel for a standard 500nm trip according to the textbook? (See Figure 12.5.)
Embry ASCI310 Module 9.1 Aircraft Performance Research Project latest 2016 December
ASCI 310: Aircraft Performance Research Project
Objectives
One of the requirements for this course is an Aircraft Performance Research Projectthat entailsplanning a flight from Denver International Airport (KDEN) to Chicago O'Hare International Airport (KORD) for a given aircraft, weather conditions, and assumptions. The objective is to apply what has been learned throughout this course. Drawing on aeronautics theory and using the performance charts and equations presented in the course, each student is to answer a sequence of questions that step through the planning process. Remember, as with all of the exercises, all work (calculations) must be shown as much as possible. After all of the questions have been answered, the next task is to create a two-dimensional representation of the flight path showing the airspeeds, distance, fuel burned, and fuel remaining for the Takeoff, Climb, Cruise, Descent, and Approach phases of the flight.
Project Files - Save all of the files to your computer or a memory device for ready access outside of this course. In Week 5, familiarize yourself the project files to get an idea of the expectations. Much of the knowledge and skills for solving this project are covered in Modules 6 through 8.
Here are some important notes for this project:
1. Max takeoff weight may not be realized taking off from a high-density altitude airfield.
2. To find out how many passengers you can transport, you need to know how much fuel you need for the flight.
3. Make sure you don’t exceed the max landing weight.
4. You might have to do some iterative calculations to complete the profile.
5. Show your work as much as possible.
6. Answers can vary due to chart interpretations and because one wrong answer will carry throughout the project. Consequently, this will be considered in the grading.
Deadline
The Aircraft Performance Research Project is due by the last day of the course. The deliverable (answers and flight profile) must be submitted using the activity link in Module 9. You may submit the deliverable as a Microsoft Word or PowerPoint file or an Adobe PDF file.
Project Evaluation
Thecompleted Project will be evaluated using this Project Evaluation Rubric on a 0 to 100-pt scale. The score on theproject is worth 15% of the course grade.
Evaluation Description Points
Questions There are eight sections. Except for questions 6.1 and 8.1, each question in each sectionis worth 1.5 points.
69
Question 6.1
Find Maximum passengers/baggage and fuel required for the flight.
3
Question 8.1
Find average takeoff acceleration using takeoff ground roll and VR.
3
Flight Profile Two-dimension representation of the flight path showing airspeed, altitude, time, distance, and fuel burned and remaining for each flight segment.
15
Style Overall Presentation 10
Total Possible Score 100
Aircraft Information
Aircraft C-9B
Engines Twin JT8D-9 engines rated at 14,500 lb static sea level
Max Ramp Gross Weight 111,000 lb
Max Takeoff Gross Weight 110,000 lb
Max Landing 99,000 lb
Empty Weight Including Aircrew 60,000 lb
Estimated Wing Area 1300 ft2
Glide Ratio at (L/D)max 17/1
Max Fuel 38,000 lb
Max Passengers 90
Assumptions
Start/Taxi Fuel 300 lb
Takeoff Fuel Burn 700 lb
Approach Fuel Burn 300 lb /approach
Average Weight per Passenger including Baggage 225 lb/per person
Fuel Required Start/Taxi Fuel +Takeoff Fuel + Climb Fuel + Cruise Fuel + Descent Fuel + Approach Fuel + 30 min reserve at Cruise Speed/Fuel Flow
KDEN Denver International Airport and Weather Information
Winds 160 deg @ 20 kts
Barometric Altimeter Setting 29.32
Temperature +30 deg
KORD Chicago International Airport and Weather Information
Winds 320 deg @ 25 kts
Barometric Altimeter Setting 30.52
Temperature 0 ºC
Winds and Temperature Aloft
Cruise FL350 Winds 240 deg @ 100 kts Temperature Standard
Climb-Assume No Winds & Temperature is ISA +15 ºC for the Climb
SECTION 1: Takeoff Questions atKDEN
Note.Assume Flaps at 15 deg.
1.1. (1.5 pts) Find Maximum Takeoff Weightfor the given conditions.Assume takeoff is at Max Recommended Takeoff weight accounting for Density altitude(see Figure 11-21).
1.2. (1.5 pts) Find Takeoff Speeds:V1, V2, VR(see Figure 11-25). Assume Min Speed due to VMCG Requirements is OK.
1.3. (1.5 pts) Find Flap Retraction Speed (KIAS).
1.4. (1.5 pts) Find Slat Retraction Speed (KIAS).
1.5. (1.5 pts) Find Critical Field Length (ft).
1.6. (1.5 pts) Find Distance to Accelerate and Stop with a Single Engine Failure at V1(ft).
1.7. (1.5 pts) Find Distance to Liftoff with Single Engine Failure at V1 and continue Takeoff(ft).
1.8. (1.5 pts) Find Two Engine Takeoff Ground Roll (ft).
1.9. (1.5 pts) Isthe runway long enough at KDEN to safely takeoff?
SECTION 2: Climb Questions (Long Range Climb to FL350)
Hint.Remember, the aircraft is taking off at a higher pressure altitude!
2.1. (1.5 pts) Find Climb Schedule (Airspeed/Mach to be flown in the Climb).
2.2. (1.5 pts) Find Time to Climb (min).
2.3. (1.5 pts) Find Distance to Climb (nm).
2.4. (1.5 pts) Find Fuel for Climb (lb).
SECTION 3: Cruise Questions (Long Range Cruise at FL350) KDEN - KORD
Note.Assume no anti-ice and two engines.
3.1. (1.5 pts) Find Cruise Indicated Airspeed (KIAS).
3.2.(1.5 pts) Find Cruise True Airspeed (KTAS).
3.3.(1.5 pts) Find Cruise Ground Speed (KGS).
3.4.(1.5 pts) Find Total Cruise Fuel Flow (lb/hr). Note, fuel flow listed is for each engine.
3.5.(1.5 pts) Find Cruise Mach (M).
3.6.(1.5 pts) Find Cruise Specific Range (nm/1000lb).
3.7.(1.5 pts) Find Maximum Level Flight Speed: Max Thrust at the Top of Climb Weight.
SECTION 4: Descent Questions (Long Range Optimum Descent from FL350)
4.1.(1.5 pts) Find Decent Schedule (Airspeed/Mach to be flown in the Descent).
4.2.(1.5 pts) Find Time to Descent (min).
4.3.(1.5 pts) Find Fuel for Descent (lb).
4.4.(1.5 pts) Find Distance for Descent (nm).
SECTION 5: Holding and Endurance
5.1.(1.5 pts) Find Max endurance and holding speed for aircraft at GW75klb@10kft Pressure Altitude.
SECTION 6: Approach and Landing (Flaps 50 deg) KORD
6.1.(3 pts) Find Maximum passengers/baggage and fuel required for flight.
Hint:Find fuel for each segment of the flight plus reserves, and then subtract from Max Recommended Takeoff weight determined in Section 1. Then divide allowable Weight by passenger Cargo Weight.
6.2.(1.5 pts) Find Reference Speed for predicted Landing Weight (KIAS).
6.3.(1.5 pts) Find Final Approach speedwith 50 degflaps (KIAS).
6.4.(1.5 pts) Find Landing DistanceFull Anti-Skid/ No Reverse Thrust/Full Spoilers(ft).
6.5.(1.5 pts) FindMax Angle of Bankfor Stick Shaker at Vref +5 for predicted Landing Weight.
SECTION 7: Lost Airspeed Indication beforeDescent
7.1.(1.5 pts) Find Cruise FL350 Target Pitch Attitude and %N1.
7.2.(1.5 pts) Find Descent Profile.
7.3.(1.5 pts) Find Terminal Area Flight Profile (0 deg Flaps).
7.4.(1.5 pts) Find Final Approach Profile (50 deg Flaps).
SECTION 8: Additional Performance Questions
8.1.(3 pts) Find average takeoff acceleration using takeoff ground roll and VR. (Hint. Convert VR to KTASand then to Ground Speed.)
8.2.(1.5 pts) Find average drag on takeoff roll assuming constant thrust. Account for reduced thrust at higher density altitude: Use Equation 6.5, let x = 0.8, and constant rolling friction.
Assume no lift on wings until rotation.
8.3.(1.5 pts) Find Stall Speed (KIAS) at Takeoff weight with flaps at 15 degand slats extended.
8.4.(1.5 pts) Find CLMAX at Takeoff weight with flaps at 15 degand slats extended.
8.5.(1.5 pts) Find Stick Shaker Speed (KIAS) at Takeoff weight with Flaps at 15 degand slats extended.
8.6.(1.5 pts) Find CL at Stick Shaker Speed with flaps at 15 degand slats extended.
8.7.(1.5 pts) Find Airspeed Envelope Maximum and Minimum Mach for Wings Level, GW 80,000 lb, andFL350 based on Buffet Boundary.
8.8.(1.5 pts) Find Maximum Load factor (g) and AOBat FL350 andGW 80,000 lb for buffet free flight.
8.9.(1.5 pts) Find Initial Climb Gradient for Takeoff Conditions fora single engine.
8.10.(1.5 pts) Find Initial Rate of Climb for a single-engine takeoff
8.11.(1.5 pts) Find Excess Thrust (lb) for initial single engine climb. Assume V= 1.23 Vs and V is converted to TAS.
8.12.(1.5 pts) Ifboth engines flameout at FL350 125 nm prior to Chicago, and you fly at best glide speed, will you make Chicago on a flameout approach?
8.13.(1.5 pts) Find Drag (Thrust Required) at (L/D)max at Sea Level Takeoff weight.
8.14.(1.5 pts) Find Temperature Ram Rise at Cruise Mach for a standard temperature probe assuming 100% recovery.
Question 1
0 / 5 pts
What are the "basic units" in the British Gravitational System (BGS) for Energy?
ft/sec
ft-lb
ft-lb/sec
lb-sec
None of the above (neither A, B, C, or D)
Question 2
0 / 5 pts
Find the Potential Energy (ft-lb) of an aircraft weighing 300,000 lbs at 5,000 ft true altitude and 200 KTS True Air Speed.
1.5 x 109 ft-lb
6 x107 ft-lb
1 x 106 ft-lb
4.67 x 107 ft-lb
Question 3
5 / 5 pts
How does a decrease in Density altitude affect parasite and induced drag airborne?
Decreases both parasite and induced Drag
Density altitude does not affect drag
Increases Parasite Drag and decreases Induced Drag
Decreases Parasite Drag and increases Induced Drag
Question 4
0 / 5 pts
Find Glide Angle at Best L/D
Given:
Weight: 300,000 lb
Wing Area: 3050 ft2
Altitude: Sea level
Temperature: Standard
CL vs. AOA Curve Figure 4.3
CL vs. CD Curve Figure 4.12
Configuration: Flaps-30 Gear Down
8 .02 deg
5.5 deg
1.37 deg
7.13 deg
Question 5
0 / 5 pts
Find best Lift-to-Drag ratio.
Givens:
Weight: 300,000 lb
Wing Area: 3,050 ft2
Altitude: Sea level
Temperature: Standard
CL vs. AOA Curve Figure 4.3
CL vs. CD Curve Figure 4.12
Configuration: Flaps-30, Gear Down
15:1
20:1
8:1
10:1
Question 6
0 / 5 pts
In order to maximize cruise range the pilot or aircraft designer should do want with the CG?
Move the CG as far aft as possible
Move the CG as far forward as possible
CG has no affect on Range; so do nothing
Move the CG as high as you can
Question 7
0 / 5 pts
What is the maximum allowable payload for this flight considering the following information?
Given:
Basic operating weight: 100,500 lb.
Maximum zero fuel weight: 138,000 lb.
Maximum landing weight: 142,000 lb.
Maximum takeoff weight: 184,200 lb.
Fuel tank load: 28,000 lb.
Estimated fuel burn en route: 25,000 lb.
37,500 lb.
38,500 lb.
55,700 lb.
27,500 lb
Question 8
0 / 5 pts
How is turbojet Thrust Specific Fuel Consumption (TSFC) affected by outside air temperature?
TSFC decreases with decreasing temperature
TSFC is unaffected by changes in temperature
TSFC increases with decreasing temperature
Question 9
5 / 5 pts
Find Fuel Flow to maintain Level Flight.
Given:
Weight: 250,000 lb
Altitude: FL250
Temperature: Standard
Airspeed: Best Endurance
CL vs. CD Curve Figure 4.5
Turbofan Thrust Figure 6.5
Configuration: Flaps 0
8575 lb/hr
6500 lb/hr
6875 lb/hr
13,000 lb/hr
Question 10
0 / 5 pts
Find Thrust Specific Fuel Consumption (TSFC).
Givens:
Altitude: FL250
Temperature: Standard
Airspeed: 0.55 Mach
Turbofan TSFC Figure 6.5
0.55
0.32
0.42
0.60
Question 11
5 / 5 pts
What is the speed of sound at sea level on a standard day?
573.80 KTAS
603.23 KTAS
661.74 KTAS
Question 12
0 / 5 pts
Find Temperature Ratio at Cruising Altitude.
Givens:
Cruising Indicated Altitude:FL 350
Outside Air Temperature at altitude: -40 deg C
Atmosphere Table 2.1
0.8091
0.7594
0.2353
0.8253
Question 13
5 / 5 pts
Given a standard day, at what altitude is the true airspeed of an aircraft approximately twice what the airspeed indicator reads?
sea level
18,000 ft MSL
20,000 ft MSL
40,000 ft MSL
Question 14
0 / 5 pts
Find Equivalent Airspeed (KEAS).
Given:
Pressure Altitude: FL350
Indicated Airspeed: 250 KIAS
Atmosphere Table 2.1
Compressibility Correction Figure 3.2
Position error correction Figure 3.1
240 KEAS
236 KEAS
260 KEAS
264 KEAS
Question 15
0 / 5 pts
What factor causes an increase in the airspeed envelope of a transport aircraft?
Decreased Weight
Increased available thrust
A & B above
Question 16
5 / 5 pts
In preparing Range and Endurance Performance Charts, what the four most important parameters?
Fuel Flow, Color of airplane, Mass, and Airspeed
Weight, Passenger loading, Altitude, and Airspeed
Fuel Flow, Weight, Pressure Altitude, and Airspeed
Sea level Pressure, Weight, Fuel Flow and Airspeed
Question 17
0 / 5 pts
What method of flight test is used to determine V2, Vx and Vy?
Saw tooth Climb
Maximum Unstick tests
Fuel Flow vs Weight
Vmc
Question 18
0 / 5 pts
Find Fuel Flow One Engine.
Given:
Weight: 300,000 lb
Cruise Chart Figure 12.8
Temperature: ISA +10 deg C
Pressure Altitude: FL 350
4983 lb/hr
5267 lb/hr
5132 lb/hr
5832 lb/hr
Question 19
0 / 5 pts
Find V1, VR , V2.
Givens:
Transport Takeoff Chart: Figure 9.19
Pressure Altitude: 5,000 ft
Temperature: 30 deg C
Configuration: Flaps 15
Weight: 300,000 lb
No wind
129, 134, 142
134, 137, 142
136, 141, 148
132, 135, 142
Question 20
0 / 5 pts
Find Descent Time (min) using the profile found on Figure 10.11 from FL350.
21 min
25 min
23 min
Question 1
5 / 5 pts
Suppose a headwind is 10% of VR. Then, there would be a _____ difference between the new and old takeoff distances.
10%
19%
21%
5%
Question 2
0 / 5 pts
Increasing takeoff weight by 10% will require a _____ increase in VR.
5%
10%
21%
12.5%
Question 3
5 / 5 pts
It is unsafe for a jet transport aircraft to depart a runway _____ balanced field length.
equal to
shorter than
longer than
Question 4
0 / 5 pts
Under a given set of conditions, using a reduced thrust setting on takeoff will _____ rotation speed (VR ).
decrease
increase
no effect on VR (increase V2 only)
Question 5
0 / 5 pts
According to FAR Part 25, how much of the takeoff distance needed to attain 35 feet and V2 can be accomplished over a clearway?
12.5%
25%
50%
5%
Question 6
0 / 5 pts
When departing a runway longer than balanced field length, selecting a higher V1 _____ accelerate go distance and _____ accelerate stop distance.
decreases; increases
increases; decreases
increases; increases
Question 7
0 / 5 pts
The aircraft manufacturer typically determines V1, V2, and VR in what order?
Note: This order is not necessarily the same in which the pilot encounters them during takeoff.
V1, V2, and VR
V1, VR, and V2
V2, VR, and V1
Question 8
0 / 5 pts
Suppose all engines of a jet transport are shutdown in flight. The pilot can maximize time aloft by flying at a speed corresponding to _____ .
( CL / CD ) ^(1/2) MAX
( CL / CD ) MAX
( CL / CD )^(3/2) MAX
Question 9
0 / 5 pts
The cost index is _____ .
the ratio of fuel cost to hourly cost
given in pounds per hour
a dimensionless ratio
Question 10
5 / 5 pts
Find Angle of Climb (deg).
Given:
Experimental Saw Tooth Climb
Pressure Altitude: 2000 ft
Climb: 1500 ft-2500 ft
Weight: 300,000 lb
Temperature: Standard
Airspeed:165 KTAS
Climb Time: 60 sec
3.43 deg
0.59 deg
9.87 deg
2.5 deg
Question 11
5 / 5 pts
While climbing at airspeed corresponding to (L / D ) MAX, equivalent airspeed (KEAS) will _____ .
stay the same
increase
decrease
Question 12
5 / 5 pts
If the cost per flight hour increases dues to aircrew costs or maintenance costs, Climb Speed, VECON, will _____ .
stay the same
increase
decrease
Question 13
0 / 5 pts
VOPT is
Best Climb Speed where Specific Excess Power, Ps, peaks with respect to energy height
Best Climb Speed where Max Excess Power peaks with respect to Altitude
Less than Vx
Less than Vy
Question 14
0 / 5 pts
If the specific range of a particular jet transport aircraft is 33.5 NAM / 1000 p while at 400 KTAS, how far will the plane be able to fly with 50,000 pounds of fuel while flying into an 80-knot headwind?
1,340 NGM
1,500 NGM
1,675 NGM
2,010 NGM
Question 15
0 / 5 pts
What are the factors to be considered in flight planning for a maximum range flight?
Jet Stream Location
Optimum Initial Cruise Altitude based on Weight
Ability to get clearance for a “Cruise Climb”
All of the Above
Question 16
0 / 5 pts
To maximize aircraft range, the best method of optimization is to _____ .
fly at a constant altitude and adjust speed to maintain VBR throughout the flight
maintain constant altitude and airspeed, decreasing angle of attack as fuel load decreases
hold a constant angle of attack correlating to best range CL and allow altitude to increase
Question 17
5 / 5 pts
When the weight of a jet transport aircraft is increased, VBE ___ and VBR ___.
increases; increases
increases; decreases
stays the same; increases
Question 18
0 / 5 pts
What is the estimated increase in the coefficient of drag due to Wave Drag while flying at 0.85 Mach?
85 % increase
25 % increase
20 % increase
15 % increase
Question 19
0 / 5 pts
If the weight of a jet transport aircraft is increased, then best endurance airspeed (VBE) _____ and endurance (hours) _____ .
increases; remains unchanged
increases; decreases
decreases; remains unchanged
Question 20
5 / 5 pts
If the weight of a jet transport aircraft is increased, then best range airspeed (VBR) _____ and range (NM) _____ .
increases; remains unchanged
increases; decreases
decreases; remains unchanged
none of the above
Comments
Content
Embry ASCI310 Full Course latest
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Embry ASCI310 Module 1.6 Discussion
1.6 - DQ: Physical Laws
62 62 unread replies. 84 84 replies.
Discussion Item
Within the context of Newton's three laws of motion, compare and contrast the motions of an apple falling off a tree to an airplane taking off.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Evaluation
Each graded discussion will be evaluated according to the attached rubric. This message will not be repeated. Please read these instructions for information on accessing the discussion rubric. (Links to an external site.)
Embry ASCI310 Module 2.5 Discussion latest 2016 December
2.5 - DQ: Atmospheric Properties and Airspeed Measurement
7070 unread replies.8181 replies.
Discussion Item
• After reading archived FAA Circular 91.XX and the Flight Safety Digest article on RVSM, comment on the significant hurdles to accurately display and accurately fly an assigned altitude.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 3.4 Discussion latest 2016 December
3.4 - DQ: Lift and Drag
7979 unread replies.9090 replies.
Discussion
• According to the Boeing Aero Magazine article on Angle of Attack (AOA), when is AOA good to use in commercial airliners? How is it useful in Military fighter jets? Comment on how you have used AOA in your own flying.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 4.6 Discussion latest 2016 December
4.6 - DQ: Engine Thrust
6969 unread replies.7676 replies.
Discussion Items
1. Compare and contrast engine specifications, including thrust, weight, and bypass ratios for the GE F404 and J85; two very common engines. What aircraft use these engines? List your source.
2. Compare and contrast the largest turbo engine to the smallest turbo engine. List your source.
3. Compare and contrast the largest turbo propeller engine to the largest reciprocating propeller engine? List your source.
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 5.4 Discussion latest 2016 December
5.4 - DQ: Weight and Balance
7575 unread replies.8484 replies.
Discussion Items
1. Where is the aircraft aerodynamic center typically located during subsonic flight and what happens if the CG is behind the aircraft's aerodynamic center?
2. What is the danger of calculating the Weight and Balance and determining that the CG is forward of the limit ? What can you do as Loadmaster or Pilot in Command to deal with this condition?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 6.5 Discussion latest 2016 December
6.5 - DQ: Takeoff and Landing
7272 unread replies.8383 replies.
Discussion Items
1. After reading this week's additional literature on takeoffs and landings, post one paragraph on your impressions, comments, or lessons learned from the readings.
2. Imagine you are the captain of a transport airplane and your balanced field length or critical field length is longer than the runway available. What should you do? What are your available options?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 7.5 Discussion latest 2016 December
7.5 - DQ: Climb and Descent
7474 unread replies.8585 replies.
Discussion Items
1. How does VOPT (Optimum Climb speed) compare to VY (Max Rate of Climb)? Most transport airplane climb schedules are based on what type profile and why?
2. What chain of events led to the Gimli Glider Incident? What were the factors that saved the airplane and passengers?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 8.3 Discussion latest 2016 December
8.3 - DQ: Range and Endurance
5151 unread replies.6565 replies.
Discussion Item
• Imagine you are flying your jet glider around the world. How can you optimize range performance in the planning and flying stages?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 9.2 Discussion latest 2016 December
9.2 - DQ: Aircraft Performance Experiences
5555 unread replies.7575 replies.
Discussion Items
1. What interesting aircraft performance stories have you experienced, heard, or read about happening at Denver International Airport (KDEN) or Chicago O'Hare International Airport (KORD)?
2. What factors from such experiences can you relate to what you have learned from completing your Aircraft Performance Project?
Your participation in this forum contributes to your Discussion grade. The Discussion grade is 10% of your course grade. Responses are going to be judged primarily for quality of analytical thought. Some emphasis is placed on writing skills to assure interpretability of your responses and also on timeliness to help foster more robust dialog.
Deadline
Respond to the discussion item and reply to your classmates by the end of this module week.
Embry ASCI310 Module 1 Assignment Exercise 1 latest 2016 December
Exercise 1: Rectilinear Motion
Background
The average accelerations of a US Navy fighter jet takeoff to an US Air Force fighter jet takeoff are very different. The aircraft conditions are the same except the Air Force fighter is on a 12,000-ft dry concrete runway and the Navy fighter is on the catapult of an aircraft carrier. (Hint: You will have to use two different methods because you are not given the catapult force, but you have the catapult distance. Assume aircraft is airborne after the catapult stroke.)
Givens:
Gross Weight (W) = 55,000 lb
Average Drag (D) = 9,000 lb
Average Friction (f) = 1,500 lb
Average Thrust (T) = 36,000 lb
Lift Off Speed ( VLO) 180 KTAS
Catapult Distance = 350 ft
1. Compute the average acceleration of the Air Force Fighter during the takeoff roll (ft/s 2).
2. What would be the length of the takeoff roll for the Air Force Fighter (ft)?
3. How long (time) would it take for the Air Force Fighter to liftoff (sec)?
4. Compute the average acceleration of the Navy Fighter during catapult launch (ft/s2).
5. How long (time in seconds) does it take for the Navy fighter to takeoff with a catapult launch?
6. Find potential, kinetic, and total energy of this aircraft after takeoff at the following conditions:
Weight = 50,000 lb
Altitude = 10,000 ft
Airspeed = 300 KTAS
7. Given conditions of #6, find new altitude if the aircraft raises the nose to capture 250 KTAS but keeps the thrust at the same setting and, for simplicity, assume the drag stays the same. Think of this as a Constant Energy Problem.
8. Find Energy Height (TE/W) of aircraft at 300 KTAS and 10,000 ft.
Embry ASCI310 Module 2.6 Assignment Exercise 2 latest 2016 December
Exercise 2: Airspeed Determination
Givens:
Altitude: FL310 (31,000 ft Pressure Altitude)
Indicated Airspeed: 250 KIAS
Indicated Outside Air Temperature (IOAT) or Total Temperature: -30 deg C
Figure 2.1 for Atmosphere
Figure 3.1 Position Errors
Figure 3.2 Compressibility Errors
Figure 11.2 or Tt= Ta(1 + .2M2) Temperature Ram Rise
1. Find CAS (Calibrated Airspeed in kts).
2. Find EAS (Equivalent Airspeed in kts).
3. Find Pressure Ratio: .
4. Find Mach.
5. Find Actual Outside Air Temperature (ambient temperature).
6. Find Temperature Ram Rise.
7. Find Density Ratio: .
8. Find TAS, True Airspeed in kts.
9. If you are landing into an airfield in mountainous terrain at afield elevation of 3,000 ftMSL (Mean Sea Level) and the field outside air temperature is -24 deg C, according to AC 91-XX Draft Appendix 2, how should you adjust your approach arrival procedures with a Final Approach Fix (FAF) at 5,000 ftMSL and your Minimum Descent Altitude (MDA) at 3500 ftMSL?
Embry ASCI310 Module 4.7 Assignment Exercise 4 latest 2016 December
Exercise 4: Thrust Available
Given Aircraft Conditions:
Gross Weight for Cruise = 300,000 lbs
Wing Area = 3050 ft2
Wing Span = 156 ft
Wing Efficiency = .80
CDp= 0.0119
Twin turbofan engine Aircraft
Thrust @ sea level = 50,000 lb/per engine
Temp-Standard
Figure 2.1
Figures 4.3 and 4.5
Figure 5.1
Figure 6.5
1. Using Figure 6.5, find Thrust Available at 100 % RPM Max Endurance Airspeed at FL350 (Both Engines). Does the Thrust Available exceed the thrust required from Exercise 3?
2. Using Figure 6.5 (Equation 6.2), find the Total Fuel Flow (both engines) to maintain Max endurance speed in Level flight at FL350?
3. What would the % thrust and % N1setting be at Max Endurance Speed, FL350? Assume Thrust available from Problem 1,Thrust Required from Exercise 3, andin Equation 6.4 use 5.0 for x for turbofan engines.
4. UsingFigure 6.5, if you lost one engine, would you be able to maintain level flight at Max Endurance Airspeed at FL250?
5. How would the Altitude (FL350 as compared to FL250) affect the Induced and Parasite drag on the aircraft atconstant true airspeed?
Embry ASCI310 Module 5.5 Assignment Exercise 5 latest 2016 December
Exercise 5: Weight and Balance
Use the aircraft specifications given below to answer the questions:
Basic operating weight 90,000 lb
Maximum zero fuel weight 120,000 lb
Maximum landing weight 140,000 lb
Maximum takeoff weight 170,000 lb
Fuel tank load 25,000 lb
Estimated fuel burn en route 15,000 lb
Field limited weight 160,000 lb
Obstacle limited weight 150,000 lb
Total Moment (takeoff) 92,437,500 lb-in.
LEMAC 600 in.
TEMAC 750 in.
Forward Cargo Station 200 in.
Aft Cargo Station 700 in.
1. What is the maximum allowable payload for this flight?
2. Assuming the aircraft is loaded with maximum allowable payload, what is the takeoff CG (inches)?
3. Assuming the aircraft is loaded with maximum allowable payload, what is the takeoff CG (percent MAC)?
4.Suppose we need to shift the CG to 20% MAC. How much weight should be moved from the aft cargo hold to the forward cargo hold?
Embry ASCI310 Module 6.6 Assignment Exercise 6 latest 2016 December
Exercise 6: Takeoff and Landing Performance
Given Conditions:
Weight 300,000 lb
Density Altitude 5,000 ft
Temperature Standard
Configuration Flaps-5
V speeds Figure 9.19
No Wind/No Slope
Thrust 103% Full
Takeoff ground roll distance 4000 ft
Balance Field Length (BFL) 7500 ft
1. Find V1, V2, VR(see Figure 9.19).
2. For a new weight of 350,000 lb and using Table 7.2 Summary of Useful Takeoff Proportions in Modern Jet Transportation Performance, find the following:
a) Takeoff Ground Roll with weight increased to 350,000 lb.
b) VR(assume Rotation Speed is solely a function of stall speed).
3. For a new weight of 300,000 lb, sea level Density Altitude,and using Table 7.2 in the Lewis textbook, find the Takeoff Ground Roll.
4. For a new weight of weight 300,000, increased wind to 20 kts of headwind, and Density Altitude of 5,000 ft, find the Takeoff Ground Roll.
5. How does an increase in Density Altitudeaffect V1, V2, VR, BFL?
6. How does an increase in Weight affect V1, V2, VR, andBFL?
7. How does a slippery runway affect V1, V2, VR, and BFL?
8. If you increase the takeoff weight by 10% (i.e., 300,000lb to 330,000 lb), what is the rule of thumb increase in takeoff distance and rotation speed in percentage?
9. If an aircraft is able to climb 35 ft after 1000 ft of horizontal travel on takeoff, what is the climb gradient (%) and climb angle (deg)?
Embry ASCI310 Module 7.6 Assignment Exercise 7 latest 2016 December
Exercise 7: Climb
1. Given conditions of “Saw-tooth” climb flight test.
Pressure Altitude-2000 ft Weight 300,000 lbs
Single engine Method Constant Airspeed Climb +/- 500 ft
Temperature:Standard (Climb from 1500 ft to 2500 ft)
Assume negligible airspeed errors due to position and compressibility
Airspeed Airspeed Climb Time Average Rate of Climb Average Rate of Climb Angle of Climb
(KIAS) (KTAS) (s) (ft/min) (kts) (deg)
140 80
160 65
180 60
190 70
Fill out the above table.
Find: (a) Indicated Airspeed for Vx(Best Angle Climb Airspeed) and Vy(Best Rate of Climb Airspeed)
(b) Angle of Climb for Vx
(c) Rate of Climb for Vy
(d) Specific Excess Power at Vy
(e) Excess Thrust at Vy and Vx
2. Follow on from Exercise 4:
Given Conditions:
Gross Weight for Cruise = 300,000 lbs
Wing Area = 3050 ft2
Wing Span = 156 ft
Wing Efficiency = .80
CDp= 0.0119
Twin turbofan engine Aircraft
Thrust @ sea level = 50,000 lb/per engine
Temp-Standard
Figure 2.1
Figure 4.3, 4.5
Figure 5.1
Figure 6.5
(a) Find Rate of Climb at Max Endurance Airspeed at FL350 100% RPM (Thrust Available from Exercise 4 and Thrust Required from Exercise 3).
(b) Find Angle of Climb at Max Endurance Airspeed at FL350 100% RPM (Thrust Available from Exercise 4 and Thrust Required from Exercise 3).
3. Find Cost Index (lb/hr) of an aircraft that has operating costs including maintenance and aircrew of $ 3,000 /hr with fuel costs of $5.00 / gallon.
Assume Jet Fuel = 6.8lb/gallon.
Embry ASCI310 Module 8.4 Assignment Exercise 8 latest 2016 December
Exercise 8: Range/Endurance
Givens Conditions:
Gross Weight for Beginning of Cruise = 300,000 lbs
Gross Weight at End of Cruise = 200,000 lbs
Altitude = FL350
Standard Conditions
Wing Area = 3050 ft2
Wing Span = 156 ft
Wing Efficiency = .75
CDp= 0.0119
Twin turbofan engines
Figure 2.1
Figure 6.5
Figure 13.2
No need to take into account Temperature Ram Rise
1. Find Equivalent Airspeed, True Airspeed, and Mach for best range at FL350 and Sea Level at W=300,000 lb. (Use Figure 13.2 and Equations 4.6, 3.8. and 3.4.)
2. Assuming constant altitude,find the best Range Equivalent Airspeed, True Airspeed, and Mach at the end of cruise for W=200,000 lb at FL350, and Sea Level. (Use Figure 13.2 and Equations 4.6, 3.8, and 3.4.)
3. Find Range (nm)at Sea Level and at constant FL350.Assume altitude remains constant, AOA remains constant, and Airspeed varies (Use Equation 13.1.)
4. Compare specific ranges at FL350 W = 300,000 lb and W = 200,000 lb. (Use Equation 12.2.)
5. Find Equivalent Airspeed, True Airspeed, and Mach for best endurance at FL350 and Sea Level at W= 300,000 lb.
6. Assuming Constant Altitude, what is best Endurance Equivalent Airspeed, True Airspeed, and Mach at W=200,000 lb?
7. Find Best Endurance (hours)at FL350 (use Equation 13.9) using the same gross weight differences.
8. How much does it cost a B-737 to carry an extra 10,000 lb of fuel for a standard 500nm trip according to the textbook? (See Figure 12.5.)
Embry ASCI310 Module 9.1 Aircraft Performance Research Project latest 2016 December
ASCI 310: Aircraft Performance Research Project
Objectives
One of the requirements for this course is an Aircraft Performance Research Projectthat entailsplanning a flight from Denver International Airport (KDEN) to Chicago O'Hare International Airport (KORD) for a given aircraft, weather conditions, and assumptions. The objective is to apply what has been learned throughout this course. Drawing on aeronautics theory and using the performance charts and equations presented in the course, each student is to answer a sequence of questions that step through the planning process. Remember, as with all of the exercises, all work (calculations) must be shown as much as possible. After all of the questions have been answered, the next task is to create a two-dimensional representation of the flight path showing the airspeeds, distance, fuel burned, and fuel remaining for the Takeoff, Climb, Cruise, Descent, and Approach phases of the flight.
Project Files - Save all of the files to your computer or a memory device for ready access outside of this course. In Week 5, familiarize yourself the project files to get an idea of the expectations. Much of the knowledge and skills for solving this project are covered in Modules 6 through 8.
Here are some important notes for this project:
1. Max takeoff weight may not be realized taking off from a high-density altitude airfield.
2. To find out how many passengers you can transport, you need to know how much fuel you need for the flight.
3. Make sure you don’t exceed the max landing weight.
4. You might have to do some iterative calculations to complete the profile.
5. Show your work as much as possible.
6. Answers can vary due to chart interpretations and because one wrong answer will carry throughout the project. Consequently, this will be considered in the grading.
Deadline
The Aircraft Performance Research Project is due by the last day of the course. The deliverable (answers and flight profile) must be submitted using the activity link in Module 9. You may submit the deliverable as a Microsoft Word or PowerPoint file or an Adobe PDF file.
Project Evaluation
Thecompleted Project will be evaluated using this Project Evaluation Rubric on a 0 to 100-pt scale. The score on theproject is worth 15% of the course grade.
Evaluation Description Points
Questions There are eight sections. Except for questions 6.1 and 8.1, each question in each sectionis worth 1.5 points.
69
Question 6.1
Find Maximum passengers/baggage and fuel required for the flight.
3
Question 8.1
Find average takeoff acceleration using takeoff ground roll and VR.
3
Flight Profile Two-dimension representation of the flight path showing airspeed, altitude, time, distance, and fuel burned and remaining for each flight segment.
15
Style Overall Presentation 10
Total Possible Score 100
Aircraft Information
Aircraft C-9B
Engines Twin JT8D-9 engines rated at 14,500 lb static sea level
Max Ramp Gross Weight 111,000 lb
Max Takeoff Gross Weight 110,000 lb
Max Landing 99,000 lb
Empty Weight Including Aircrew 60,000 lb
Estimated Wing Area 1300 ft2
Glide Ratio at (L/D)max 17/1
Max Fuel 38,000 lb
Max Passengers 90
Assumptions
Start/Taxi Fuel 300 lb
Takeoff Fuel Burn 700 lb
Approach Fuel Burn 300 lb /approach
Average Weight per Passenger including Baggage 225 lb/per person
Fuel Required Start/Taxi Fuel +Takeoff Fuel + Climb Fuel + Cruise Fuel + Descent Fuel + Approach Fuel + 30 min reserve at Cruise Speed/Fuel Flow
KDEN Denver International Airport and Weather Information
Winds 160 deg @ 20 kts
Barometric Altimeter Setting 29.32
Temperature +30 deg
KORD Chicago International Airport and Weather Information
Winds 320 deg @ 25 kts
Barometric Altimeter Setting 30.52
Temperature 0 ºC
Winds and Temperature Aloft
Cruise FL350 Winds 240 deg @ 100 kts Temperature Standard
Climb-Assume No Winds & Temperature is ISA +15 ºC for the Climb
SECTION 1: Takeoff Questions atKDEN
Note.Assume Flaps at 15 deg.
1.1. (1.5 pts) Find Maximum Takeoff Weightfor the given conditions.Assume takeoff is at Max Recommended Takeoff weight accounting for Density altitude(see Figure 11-21).
1.2. (1.5 pts) Find Takeoff Speeds:V1, V2, VR(see Figure 11-25). Assume Min Speed due to VMCG Requirements is OK.
1.3. (1.5 pts) Find Flap Retraction Speed (KIAS).
1.4. (1.5 pts) Find Slat Retraction Speed (KIAS).
1.5. (1.5 pts) Find Critical Field Length (ft).
1.6. (1.5 pts) Find Distance to Accelerate and Stop with a Single Engine Failure at V1(ft).
1.7. (1.5 pts) Find Distance to Liftoff with Single Engine Failure at V1 and continue Takeoff(ft).
1.8. (1.5 pts) Find Two Engine Takeoff Ground Roll (ft).
1.9. (1.5 pts) Isthe runway long enough at KDEN to safely takeoff?
SECTION 2: Climb Questions (Long Range Climb to FL350)
Hint.Remember, the aircraft is taking off at a higher pressure altitude!
2.1. (1.5 pts) Find Climb Schedule (Airspeed/Mach to be flown in the Climb).
2.2. (1.5 pts) Find Time to Climb (min).
2.3. (1.5 pts) Find Distance to Climb (nm).
2.4. (1.5 pts) Find Fuel for Climb (lb).
SECTION 3: Cruise Questions (Long Range Cruise at FL350) KDEN - KORD
Note.Assume no anti-ice and two engines.
3.1. (1.5 pts) Find Cruise Indicated Airspeed (KIAS).
3.2.(1.5 pts) Find Cruise True Airspeed (KTAS).
3.3.(1.5 pts) Find Cruise Ground Speed (KGS).
3.4.(1.5 pts) Find Total Cruise Fuel Flow (lb/hr). Note, fuel flow listed is for each engine.
3.5.(1.5 pts) Find Cruise Mach (M).
3.6.(1.5 pts) Find Cruise Specific Range (nm/1000lb).
3.7.(1.5 pts) Find Maximum Level Flight Speed: Max Thrust at the Top of Climb Weight.
SECTION 4: Descent Questions (Long Range Optimum Descent from FL350)
4.1.(1.5 pts) Find Decent Schedule (Airspeed/Mach to be flown in the Descent).
4.2.(1.5 pts) Find Time to Descent (min).
4.3.(1.5 pts) Find Fuel for Descent (lb).
4.4.(1.5 pts) Find Distance for Descent (nm).
SECTION 5: Holding and Endurance
5.1.(1.5 pts) Find Max endurance and holding speed for aircraft at GW75klb@10kft Pressure Altitude.
SECTION 6: Approach and Landing (Flaps 50 deg) KORD
6.1.(3 pts) Find Maximum passengers/baggage and fuel required for flight.
Hint:Find fuel for each segment of the flight plus reserves, and then subtract from Max Recommended Takeoff weight determined in Section 1. Then divide allowable Weight by passenger Cargo Weight.
6.2.(1.5 pts) Find Reference Speed for predicted Landing Weight (KIAS).
6.3.(1.5 pts) Find Final Approach speedwith 50 degflaps (KIAS).
6.4.(1.5 pts) Find Landing DistanceFull Anti-Skid/ No Reverse Thrust/Full Spoilers(ft).
6.5.(1.5 pts) FindMax Angle of Bankfor Stick Shaker at Vref +5 for predicted Landing Weight.
SECTION 7: Lost Airspeed Indication beforeDescent
7.1.(1.5 pts) Find Cruise FL350 Target Pitch Attitude and %N1.
7.2.(1.5 pts) Find Descent Profile.
7.3.(1.5 pts) Find Terminal Area Flight Profile (0 deg Flaps).
7.4.(1.5 pts) Find Final Approach Profile (50 deg Flaps).
SECTION 8: Additional Performance Questions
8.1.(3 pts) Find average takeoff acceleration using takeoff ground roll and VR. (Hint. Convert VR to KTASand then to Ground Speed.)
8.2.(1.5 pts) Find average drag on takeoff roll assuming constant thrust. Account for reduced thrust at higher density altitude: Use Equation 6.5, let x = 0.8, and constant rolling friction.
Assume no lift on wings until rotation.
8.3.(1.5 pts) Find Stall Speed (KIAS) at Takeoff weight with flaps at 15 degand slats extended.
8.4.(1.5 pts) Find CLMAX at Takeoff weight with flaps at 15 degand slats extended.
8.5.(1.5 pts) Find Stick Shaker Speed (KIAS) at Takeoff weight with Flaps at 15 degand slats extended.
8.6.(1.5 pts) Find CL at Stick Shaker Speed with flaps at 15 degand slats extended.
8.7.(1.5 pts) Find Airspeed Envelope Maximum and Minimum Mach for Wings Level, GW 80,000 lb, andFL350 based on Buffet Boundary.
8.8.(1.5 pts) Find Maximum Load factor (g) and AOBat FL350 andGW 80,000 lb for buffet free flight.
8.9.(1.5 pts) Find Initial Climb Gradient for Takeoff Conditions fora single engine.
8.10.(1.5 pts) Find Initial Rate of Climb for a single-engine takeoff
8.11.(1.5 pts) Find Excess Thrust (lb) for initial single engine climb. Assume V= 1.23 Vs and V is converted to TAS.
8.12.(1.5 pts) Ifboth engines flameout at FL350 125 nm prior to Chicago, and you fly at best glide speed, will you make Chicago on a flameout approach?
8.13.(1.5 pts) Find Drag (Thrust Required) at (L/D)max at Sea Level Takeoff weight.
8.14.(1.5 pts) Find Temperature Ram Rise at Cruise Mach for a standard temperature probe assuming 100% recovery.
Question 1
0 / 5 pts
What are the "basic units" in the British Gravitational System (BGS) for Energy?
ft/sec
ft-lb
ft-lb/sec
lb-sec
None of the above (neither A, B, C, or D)
Question 2
0 / 5 pts
Find the Potential Energy (ft-lb) of an aircraft weighing 300,000 lbs at 5,000 ft true altitude and 200 KTS True Air Speed.
1.5 x 109 ft-lb
6 x107 ft-lb
1 x 106 ft-lb
4.67 x 107 ft-lb
Question 3
5 / 5 pts
How does a decrease in Density altitude affect parasite and induced drag airborne?
Decreases both parasite and induced Drag
Density altitude does not affect drag
Increases Parasite Drag and decreases Induced Drag
Decreases Parasite Drag and increases Induced Drag
Question 4
0 / 5 pts
Find Glide Angle at Best L/D
Given:
Weight: 300,000 lb
Wing Area: 3050 ft2
Altitude: Sea level
Temperature: Standard
CL vs. AOA Curve Figure 4.3
CL vs. CD Curve Figure 4.12
Configuration: Flaps-30 Gear Down
8 .02 deg
5.5 deg
1.37 deg
7.13 deg
Question 5
0 / 5 pts
Find best Lift-to-Drag ratio.
Givens:
Weight: 300,000 lb
Wing Area: 3,050 ft2
Altitude: Sea level
Temperature: Standard
CL vs. AOA Curve Figure 4.3
CL vs. CD Curve Figure 4.12
Configuration: Flaps-30, Gear Down
15:1
20:1
8:1
10:1
Question 6
0 / 5 pts
In order to maximize cruise range the pilot or aircraft designer should do want with the CG?
Move the CG as far aft as possible
Move the CG as far forward as possible
CG has no affect on Range; so do nothing
Move the CG as high as you can
Question 7
0 / 5 pts
What is the maximum allowable payload for this flight considering the following information?
Given:
Basic operating weight: 100,500 lb.
Maximum zero fuel weight: 138,000 lb.
Maximum landing weight: 142,000 lb.
Maximum takeoff weight: 184,200 lb.
Fuel tank load: 28,000 lb.
Estimated fuel burn en route: 25,000 lb.
37,500 lb.
38,500 lb.
55,700 lb.
27,500 lb
Question 8
0 / 5 pts
How is turbojet Thrust Specific Fuel Consumption (TSFC) affected by outside air temperature?
TSFC decreases with decreasing temperature
TSFC is unaffected by changes in temperature
TSFC increases with decreasing temperature
Question 9
5 / 5 pts
Find Fuel Flow to maintain Level Flight.
Given:
Weight: 250,000 lb
Altitude: FL250
Temperature: Standard
Airspeed: Best Endurance
CL vs. CD Curve Figure 4.5
Turbofan Thrust Figure 6.5
Configuration: Flaps 0
8575 lb/hr
6500 lb/hr
6875 lb/hr
13,000 lb/hr
Question 10
0 / 5 pts
Find Thrust Specific Fuel Consumption (TSFC).
Givens:
Altitude: FL250
Temperature: Standard
Airspeed: 0.55 Mach
Turbofan TSFC Figure 6.5
0.55
0.32
0.42
0.60
Question 11
5 / 5 pts
What is the speed of sound at sea level on a standard day?
573.80 KTAS
603.23 KTAS
661.74 KTAS
Question 12
0 / 5 pts
Find Temperature Ratio at Cruising Altitude.
Givens:
Cruising Indicated Altitude:FL 350
Outside Air Temperature at altitude: -40 deg C
Atmosphere Table 2.1
0.8091
0.7594
0.2353
0.8253
Question 13
5 / 5 pts
Given a standard day, at what altitude is the true airspeed of an aircraft approximately twice what the airspeed indicator reads?
sea level
18,000 ft MSL
20,000 ft MSL
40,000 ft MSL
Question 14
0 / 5 pts
Find Equivalent Airspeed (KEAS).
Given:
Pressure Altitude: FL350
Indicated Airspeed: 250 KIAS
Atmosphere Table 2.1
Compressibility Correction Figure 3.2
Position error correction Figure 3.1
240 KEAS
236 KEAS
260 KEAS
264 KEAS
Question 15
0 / 5 pts
What factor causes an increase in the airspeed envelope of a transport aircraft?
Decreased Weight
Increased available thrust
A & B above
Question 16
5 / 5 pts
In preparing Range and Endurance Performance Charts, what the four most important parameters?
Fuel Flow, Color of airplane, Mass, and Airspeed
Weight, Passenger loading, Altitude, and Airspeed
Fuel Flow, Weight, Pressure Altitude, and Airspeed
Sea level Pressure, Weight, Fuel Flow and Airspeed
Question 17
0 / 5 pts
What method of flight test is used to determine V2, Vx and Vy?
Saw tooth Climb
Maximum Unstick tests
Fuel Flow vs Weight
Vmc
Question 18
0 / 5 pts
Find Fuel Flow One Engine.
Given:
Weight: 300,000 lb
Cruise Chart Figure 12.8
Temperature: ISA +10 deg C
Pressure Altitude: FL 350
4983 lb/hr
5267 lb/hr
5132 lb/hr
5832 lb/hr
Question 19
0 / 5 pts
Find V1, VR , V2.
Givens:
Transport Takeoff Chart: Figure 9.19
Pressure Altitude: 5,000 ft
Temperature: 30 deg C
Configuration: Flaps 15
Weight: 300,000 lb
No wind
129, 134, 142
134, 137, 142
136, 141, 148
132, 135, 142
Question 20
0 / 5 pts
Find Descent Time (min) using the profile found on Figure 10.11 from FL350.
21 min
25 min
23 min
Question 1
5 / 5 pts
Suppose a headwind is 10% of VR. Then, there would be a _____ difference between the new and old takeoff distances.
10%
19%
21%
5%
Question 2
0 / 5 pts
Increasing takeoff weight by 10% will require a _____ increase in VR.
5%
10%
21%
12.5%
Question 3
5 / 5 pts
It is unsafe for a jet transport aircraft to depart a runway _____ balanced field length.
equal to
shorter than
longer than
Question 4
0 / 5 pts
Under a given set of conditions, using a reduced thrust setting on takeoff will _____ rotation speed (VR ).
decrease
increase
no effect on VR (increase V2 only)
Question 5
0 / 5 pts
According to FAR Part 25, how much of the takeoff distance needed to attain 35 feet and V2 can be accomplished over a clearway?
12.5%
25%
50%
5%
Question 6
0 / 5 pts
When departing a runway longer than balanced field length, selecting a higher V1 _____ accelerate go distance and _____ accelerate stop distance.
decreases; increases
increases; decreases
increases; increases
Question 7
0 / 5 pts
The aircraft manufacturer typically determines V1, V2, and VR in what order?
Note: This order is not necessarily the same in which the pilot encounters them during takeoff.
V1, V2, and VR
V1, VR, and V2
V2, VR, and V1
Question 8
0 / 5 pts
Suppose all engines of a jet transport are shutdown in flight. The pilot can maximize time aloft by flying at a speed corresponding to _____ .
( CL / CD ) ^(1/2) MAX
( CL / CD ) MAX
( CL / CD )^(3/2) MAX
Question 9
0 / 5 pts
The cost index is _____ .
the ratio of fuel cost to hourly cost
given in pounds per hour
a dimensionless ratio
Question 10
5 / 5 pts
Find Angle of Climb (deg).
Given:
Experimental Saw Tooth Climb
Pressure Altitude: 2000 ft
Climb: 1500 ft-2500 ft
Weight: 300,000 lb
Temperature: Standard
Airspeed:165 KTAS
Climb Time: 60 sec
3.43 deg
0.59 deg
9.87 deg
2.5 deg
Question 11
5 / 5 pts
While climbing at airspeed corresponding to (L / D ) MAX, equivalent airspeed (KEAS) will _____ .
stay the same
increase
decrease
Question 12
5 / 5 pts
If the cost per flight hour increases dues to aircrew costs or maintenance costs, Climb Speed, VECON, will _____ .
stay the same
increase
decrease
Question 13
0 / 5 pts
VOPT is
Best Climb Speed where Specific Excess Power, Ps, peaks with respect to energy height
Best Climb Speed where Max Excess Power peaks with respect to Altitude
Less than Vx
Less than Vy
Question 14
0 / 5 pts
If the specific range of a particular jet transport aircraft is 33.5 NAM / 1000 p while at 400 KTAS, how far will the plane be able to fly with 50,000 pounds of fuel while flying into an 80-knot headwind?
1,340 NGM
1,500 NGM
1,675 NGM
2,010 NGM
Question 15
0 / 5 pts
What are the factors to be considered in flight planning for a maximum range flight?
Jet Stream Location
Optimum Initial Cruise Altitude based on Weight
Ability to get clearance for a “Cruise Climb”
All of the Above
Question 16
0 / 5 pts
To maximize aircraft range, the best method of optimization is to _____ .
fly at a constant altitude and adjust speed to maintain VBR throughout the flight
maintain constant altitude and airspeed, decreasing angle of attack as fuel load decreases
hold a constant angle of attack correlating to best range CL and allow altitude to increase
Question 17
5 / 5 pts
When the weight of a jet transport aircraft is increased, VBE ___ and VBR ___.
increases; increases
increases; decreases
stays the same; increases
Question 18
0 / 5 pts
What is the estimated increase in the coefficient of drag due to Wave Drag while flying at 0.85 Mach?
85 % increase
25 % increase
20 % increase
15 % increase
Question 19
0 / 5 pts
If the weight of a jet transport aircraft is increased, then best endurance airspeed (VBE) _____ and endurance (hours) _____ .
increases; remains unchanged
increases; decreases
decreases; remains unchanged
Question 20
5 / 5 pts
If the weight of a jet transport aircraft is increased, then best range airspeed (VBR) _____ and range (NM) _____ .
increases; remains unchanged
increases; decreases
decreases; remains unchanged
none of the above
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