Embry ASCI310 Complete Course latest

Embry ASCI310 Complete Course latest

 

 

Embry ASCI310 Module 16 Discussion  

16 – DQ: Physical Laws

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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 25 Discussion latest 2016 December

25 – DQ: Atmospheric Properties and Airspeed Measurement

7070 unread replies8181 replies

Discussion Item

  • After reading archived FAA Circular 91XX 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 34 Discussion latest 2016 December

34 – DQ: Lift and Drag

7979 unread replies9090 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 46 Discussion latest 2016 December

46 – DQ: Engine Thrust

6969 unread replies7676 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 54 Discussion latest 2016 December

54 – DQ: Weight and Balance

7575 unread replies8484 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 65 Discussion latest 2016 December

65 – DQ: Takeoff and Landing

7272 unread replies8383 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 75 Discussion latest 2016 December

75 – DQ: Climb and Descent

7474 unread replies8585 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 83 Discussion latest 2016 December

83 – DQ: Range and Endurance

5151 unread replies6565 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 92 Discussion latest 2016 December

92 – DQ: Aircraft Performance Experiences

5555 unread replies7575 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 26 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 21 for Atmosphere
Figure 31 Position Errors
Figure 32 Compressibility Errors
Figure 112 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 47 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= 00119

Twin turbofan engine Aircraft

Thrust @ sea level = 50,000 lb/per engine

Temp-Standard

Figure 21

Figures 43 and 45

Figure 51

Figure 65

1 Using Figure 65, 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 65 (Equation 62), 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 64 use 50 for x for turbofan engines

4 UsingFigure 65, 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 55 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)?

4Suppose 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 66 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 919

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 919)

2 For a new weight of 350,000 lb and using Table 72 Summary of Useful Takeoff Proportions in Modern Jet Transportation Performance, find the following:

  1. a) Takeoff Ground Roll with weight increased to 350,000 lb
  2. 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 72 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% (ie, 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 76 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= 00119

Twin turbofan engine Aircraft

Thrust @ sea level = 50,000 lb/per engine

Temp-Standard

Figure 21

Figure 43, 45

Figure 51

Figure 65

(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 $500 / gallon

Assume Jet Fuel = 68lb/gallon

Embry ASCI310 Module 84 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= 00119

Twin turbofan engines

Figure 21

Figure 65

Figure 132

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 132 and Equations 46, 38 and 34)

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 132 and Equations 46, 38, and 34)

3 Find Range (nm)at Sea Level and at constant FL350Assume altitude remains constant, AOA remains constant, and Airspeed varies (Use Equation 131)

4 Compare specific ranges at FL350 W = 300,000 lb and W = 200,000 lb (Use Equation 122)

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 139) 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 125)

Embry ASCI310 Module 91 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 61 and 81, each question in each sectionis worth 15 points 69
Question 61 Find Maximum passengers/baggage and fuel required for the flight 3
Question 81 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 2932
Temperature +30 deg
KORD Chicago International Airport and Weather Information
Winds 320 deg @ 25 kts
Barometric Altimeter Setting 3052
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

NoteAssume Flaps at 15 deg

11 (15 pts) Find Maximum Takeoff Weightfor the given conditionsAssume takeoff is at Max Recommended Takeoff weight accounting for Density altitude(see Figure 11-21)

12 (15 pts) Find Takeoff Speeds:V1, V2, VR(see Figure 11-25) Assume Min Speed due to VMCG Requirements is OK

13 (15 pts) Find Flap Retraction Speed (KIAS)

14 (15 pts) Find Slat Retraction Speed (KIAS)

15 (15 pts) Find Critical Field Length (ft)

16 (15 pts) Find Distance to Accelerate and Stop with a Single Engine Failure at V1(ft)

17 (15 pts) Find Distance to Liftoff with Single Engine Failure at V1 and continue Takeoff(ft)

18 (15 pts) Find Two Engine Takeoff Ground Roll (ft)

19 (15 pts) Isthe runway long enough at KDEN to safely takeoff?

SECTION 2: Climb Questions (Long Range Climb to FL350)

HintRemember, the aircraft is taking off at a higher pressure altitude!

21 (15 pts) Find Climb Schedule (Airspeed/Mach to be flown in the Climb)

22 (15 pts) Find Time to Climb (min)

23 (15 pts) Find Distance to Climb (nm)

24 (15 pts) Find Fuel for Climb (lb)

SECTION 3: Cruise Questions (Long Range Cruise at FL350) KDEN – KORD

NoteAssume no anti-ice and two engines

31 (15 pts) Find Cruise Indicated Airspeed (KIAS)

32(15 pts) Find Cruise True Airspeed (KTAS)

33(15 pts) Find Cruise Ground Speed (KGS)

34(15 pts) Find Total Cruise Fuel Flow (lb/hr) Note, fuel flow listed is for each engine

35(15 pts) Find Cruise Mach (M)

36(15 pts) Find Cruise Specific Range (nm/1000lb)

37(15 pts) Find Maximum Level Flight Speed: Max Thrust at the Top of Climb Weight

SECTION 4: Descent Questions (Long Range Optimum Descent from FL350)

41(15 pts) Find Decent Schedule (Airspeed/Mach to be flown in the Descent)

42(15 pts) Find Time to Descent (min)

43(15 pts) Find Fuel for Descent (lb)

44(15 pts) Find Distance for Descent (nm)

SECTION 5: Holding and Endurance

51(15 pts) Find Max endurance and holding speed for aircraft at GW75klb@10kft Pressure Altitude

SECTION 6: Approach and Landing (Flaps 50 deg) KORD

61(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

62(15 pts) Find Reference Speed for predicted Landing Weight (KIAS)

63(15 pts) Find Final Approach speedwith 50 degflaps (KIAS)

64(15 pts) Find Landing DistanceFull Anti-Skid/ No Reverse Thrust/Full Spoilers(ft)

65(15 pts) FindMax Angle of Bankfor Stick Shaker at Vref +5 for predicted Landing Weight

SECTION 7: Lost Airspeed Indication beforeDescent

71(15 pts) Find Cruise FL350 Target Pitch Attitude and %N1

72(15 pts) Find Descent Profile

73(15 pts) Find Terminal Area Flight Profile (0 deg Flaps)

74(15 pts) Find Final Approach Profile (50 deg Flaps)

SECTION 8: Additional Performance Questions

81(3 pts) Find average takeoff acceleration using takeoff ground roll and VR (Hint Convert VR to KTASand then to Ground Speed)

82(15 pts) Find average drag on takeoff roll assuming constant thrust Account for reduced thrust at higher density altitude: Use Equation 65, let x = 08, and constant rolling friction

Assume no lift on wings until rotation

83(15 pts) Find Stall Speed (KIAS) at Takeoff weight with flaps at 15 degand slats extended

84(15 pts) Find CLMAX at Takeoff weight with flaps at 15 degand slats extended

85(15 pts) Find Stick Shaker Speed (KIAS) at Takeoff weight with Flaps at 15 degand slats extended

86(15 pts) Find CL at Stick Shaker Speed with flaps at 15 degand slats extended

87(15 pts) Find Airspeed Envelope Maximum and Minimum Mach for Wings Level, GW 80,000 lb, andFL350 based on Buffet Boundary

88(15 pts) Find Maximum Load factor (g) and AOBat FL350 andGW 80,000 lb for buffet free flight

89(15 pts) Find Initial Climb Gradient for Takeoff Conditions fora single engine

810(15 pts) Find Initial Rate of Climb for a single-engine takeoff

811(15 pts) Find Excess Thrust (lb) for initial single engine climb Assume V= 123 Vs and V is converted to TAS

812(15 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?

813(15 pts) Find Drag (Thrust Required) at (L/D)max at Sea Level Takeoff weight

814(15 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

15 x 109 ft-lb

6 x107 ft-lb

1 x 106 ft-lb

467 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 43

CL vs CD Curve Figure 412

Configuration: Flaps-30 Gear Down

8 02 deg

55 deg

137 deg

713 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 43

CL vs CD Curve Figure 412

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 45

Turbofan Thrust Figure 65

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: 055 Mach

Turbofan TSFC Figure 65

055

032

042

060

Question 11

5 / 5 pts

What is the speed of sound at sea level on a standard day?

57380 KTAS

60323 KTAS

66174 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 21

08091

07594

02353

08253

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 21

Compressibility Correction Figure 32

Position error correction Figure 31

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 128

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 919

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 1011 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%

125%

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?

125%

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

343 deg

059 deg

987 deg

25 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 335 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 085 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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