8.1 Physics Of The Atmosphere1. List the layers of the atmosphere & how far they extend from the surface of the earth?

2. Most Commercial aircraft fly up to ___________ ft, with some military aircraft flying up to _______ft.

3. The characteristic make-up of the atmosphere is:

a. 78% nitrogen, 21% oxygen & 1% other gasesb. 78% nitrogen, 21% other gases & 1% nitrogenc. 78% oxygen, 21% nitrogen & 1% other gases

4. What is the relationship between; pressure, density & temperature as altitude increases?

5. Where is more lift & thrust generated in terms of altitude?

a. 30,000ftb. 15,000ftc. 5,000ft

6. What are the overall effects of humidity in relation to air density?

7. How is density influenced by:

I. Temperature

II. Pressure

8. What are the ISA values at Sea Level (SL)?

I. Pressure - II. Temperature - III. Temperature Lapse Rate - IV. Density - V. Speed Of Sound

9. Explain the concept of Pressure Altitude?

10. Complete the table below for ISA conditions:

8.2 Aerodynamics Airflow Around A Body & Boundary Layer11. Laminar flow, is also known as ____________ flow, when all of the particles of the fluid move in continuous ____________ lines with the air moving _______________ over an object.

12. What type of airflow causes the highest drag?

I. Laminar flowII. Free Stream Airflow (FSA)III. Turbulent Flow

13. In terms of the boundary layer & FSA, where is the air at its slowest velocity?

14. How is the Boundary layer defined?

15. What is the air flow Transition point?

16. Why is it important that the turbulent airflow within the Boundary Layer has more kinetic energy than in the Laminar Flow region?

17. State the equation of continuity & what remains constant in a moving mass of air?

18. In terms of Bernoullis Therom, pressure energy is?

a. Energy due to height or positionb. Energy due to movement of a moving fluidc. Energy stored in a non-moving fluid

19. State Bernoullis Therom formulae

8.2 Aerodynamics Aircraft Terminology20. In terms of Primary & Secondary flight controls, what are considered Primary?

21. Identify four factors that affect wing position during aircraft design:

I. II. III. IV.

22. State the difference between Gross Wing Area (S) & Net Wing Area

23. If the span of a wing (b) is 15m & the Average Chord (Cav) is 1.75m, calculate the Gross Wing Area (S)

24. From the dimension provided in Q23. Calculate the Aspect Ratio (AR) of the wingspan

25. An aircraft has a Gross Wing Area of 25m^2, with an average chord of 2m, calculate the Aspect Ratio (AR)

26. Which aircraft from the calculations in Q24. & Q25 has the highest AR & therefore highest stability/glide profile?

27. The TIP Chord of an aircraft wing is 0.75, with a Root Chord of 6m, calculate the Taper Ratio

28. The angle of Sweepback for a wing is normally ____% of the wing _________ perpendicular to an aircrafts ___________ axis

29. An aircraft has a Mean Aerodynamic Chord (MAC) of 10m, where should the Aircraft Centre Of Gravity (C of G) be located?

30. Using the diagram below; measure to physically determine the MAC & indicate where the C Of G should be if it is 25% behind the Leading Edge.

31. Draw a wing cross section (shape) for a heavy, low speed aircraft, indicating where the maximum thickness would be.

32. You are to design a wing for a transport aircraft that will be cruising at speeds approaching transonic or supersonic. Draw the cross section of the wing, indicating the point of maximum thickness.

33. In the Diagram below, draw OR indicate the following:

I. Chord LineII. Mean Camber LineIII. Maximum Camber & ThicknessIV. Leading & Trailing EdgeV. Fineness & Maximum Thickness Chord Ratio

8.2 Aerodynamics Thrust, Weight & Aerodynamic Resultant34. Thrust is produced by an engine, forcing a _____ of ____ to the ______ of an aircraft. A propeller _______ a ______ mass of air by a relatively __________ amount, which is the opposite to a turbojet engine.

35. What direction does the force of weight act?a. It depends on the bank angle of the aircraftb. Always parallel to the flight pathc. Always acts toward the centre of the earth

36. During turning manoeuvers of an aircraft, additional factors, which need to be taken into account are?

37. An aircraft is in straight and level flight at a constant speed, following the pilot applying thrust using the throttle, the aircraft will?a. Remain in straight & level flightb. Descend to a lower altitude, due to the additional aerodynamic dragc. Climb, due to the increase in air velocity of the aerofoil.

8.2 Aerodynamics - Lift, Drag & Stall

38. In relation to Relative Air Flow (RAF), how does lift act?a. Perpendicular to the RAFb. Parallel to the RAFc. In the opposite direction to the RAF

39. The lower surface of an aerofoil, resembles the ___________ part of a venturi, whilst the upper surface resembles the _________ part of a venture.

40. At which point when airflow approaches an aerofoil does the air flow come to rest & what is the value of the static pressure?

41. Draw an aerofoil & indicate: Up-wash, Down-wash, stagnation Points & dividing streamlines.

42. The Angle of Attack is the angle:a. Between the Relative Air Flow (RAF) & the aircraft centre lineb. Between the RAF & the Aerofoil Chord linec. Between the aircraft centre line & the aerofoil Chord line

43. Describe (draw) the shape of aerofoil, which will produce aerodynamic lift with an AOA of zero degrees?

44. Identify the two principle factors in determining, velocity & therefore lift for an aerofoil?

45. What is the length of the pressure vector dependant on & what is the value at any stagnation point?

46. Generally, as the AOA increases for an Asymmetrical wing, describe what happens to the pressure envelope, in terms of the pressure vectors and the position

47. For a typical aerofoil moving beyond 15 - 18 degrees, known as the ______ angle __ _________, the majority of the airflow across the upper surface breaks down into _______ _________ flow.

48. State the values of zero lift angle for a Symmetrical & Asymmetrical wing.

49. Draw an Asymmetrical aerofoil at 10 degrees AOA, with a lift vector of 10 & drag vector of 2. Show the resulting Total Reaction (TR) & measure its vector size, taking care on deciding the Centre Of Pressure (CP)

50. Explain the cause of trailing edge & wing tip vorticies.

51. What affects the pressure differential between the upper & lower part of a wing surface?a. The wing Planform shapeb. The cross section shape of the wingc. The material of the wing

52. You are required to design a wing, which produces little or no wing tip vorticies, therefore reducing drag. Identify the wing shape that you would use.

53. State the formulae for lift & lift co-efficient & what this takes into account

54. How can you determine the effect of AOA with the Co-efficient of lift (CL)

55. In the figure below, indicate the critical angle & CL (max). Which wing type does this represent?

Module 8: Self-Assessment Workbook

M8_201410 21

Alongside The Drag Enter: Causes & Factors Profile Drag + Interference Drag =Parasite Drag

56. The length of an object compared to its thickness is known as the __________ ratio, where the least amount of drag will occur with a fineness ratio of around __ to __

57. Explain the formation of induced downwash on an aircraft wing, indicating the direction of vorticies when viewed from behind an aircraft

58. If the speed of an aircraft is doubled, what happens to the dynamic pressure and therefore the co-efficient of lift? In your answer state the formulae for the Co-efficient of lift.

59. What is the relationship between Induced Drag & Speed & what other factors change induced drag?

60. Washout is the twisting of a wingtip during manufacture, which means that:

a. The AOA at the wingtip is greater than at the wing root, reducing the size of vorticies around the wingtip.b. The AOA at the wingtip is smaller than at the wing root, reducing the size of vorticies around the wingtipc. The AOA at the wingtip is greater than at the wing root, increasing the size of vorticies around the wingtip

61. Label the diagram below for: Profile, Induced & Total Drag, Minimum Drag Speed (VIMD) & Minimum Drag Force (in pounds).

62. What factors affect actual drag & is there a comparison with factors affecting Lift?

63. State the formulae for Drag, is there a comparison with Lift, explain your answer?

64. State the formulae for the Lift/Drag Ratio & where is the greatest aerodynamic efficiency?

65. From the graph below, identify: Maximum Lift AOA & Co-efficient, Minimum Drag AOA & Co-efficient.

66. Stall is a phenomenon of _________ __________ _____________ and occurs at the ________ angle of _________, when the ________ surface of the aerofoil is predominantly covered in __________ airflow.

67. Boundary layer separation is produced as a result of:a. The adverse pressure gradient, which opposes the flow of the boundary layerb. The adverse pressure gradient, which assists the flow of the boundary layerc. The adverse pressure gradient, which opposes the separation of the boundary layer

68. Ideally the adverse pressure gradient should extend from?a. The point of maximum air pressure to the rear of the aerofoil at the stagnation pointb. The point of minimum air pressure to the leading edge stagnation pointc. The point of minimum air pressure to the rear of the aerofoil at the stagnation point

69. Draw an aerofoil and show the: Transition point, Separation Point & where you would anticipate Reverse flow to occur.

70. With an increasing angle of attack, what happens to the: I. Adverse pressure gradient?II. Separation point?III. Pressure distribution curve?

71. Typically, what is the stalling angle of attack for most aerofoils & when will this change?

72. How can the lift formulae be changed to represent the angle of attack?

73. Show, through formulae, how the weight of an aircraft has an effect on the stall speed and the relationship of weight and stall speed.

74. For an aircraft with a load factor (n) of 9g and a basic stall speed (Vbasic) of 65 knots, calculate the Manouvere stall speed (VM)? What does this demonstrate about the relationship of Load factor and Stall Speed?

75. Which of the following will reduce the occurrence of tip stall?a. Washout, Root Spoilers, wing fencesb. Root Spoilers, Change in Aerofoil section, Washoutc. Change in aerofoil section, Root Spoilers, Fairings

76. What is stall buffet dependant on?

77. Name three types of stall warning devices that could be fitted to an aircraft.I. II. III.

78. Name three types of ice, which can form on aircraft aerodynamic surfaces & which is the most difficult to remove.

8.3 Theory of Flight Level Flight Conditions79. On the diagram below, indicate where the forces act through & which is the largest couple vector?

80. Indicate on the diagram, the effect of moving the Lift vector behind & in front of the Weight vector (Couple), also the Thrust vector above and below the Drag vector (Couple).

81. Explain the effect that speed and weight reduction has on an aircraft in level flight, in terms of the angle of attack.

82. The ratio of Total Lift to Aircraft Weight, results in the _______ _________. This should always be _____________ than ______.

8.3 Theory Of Flight - Manoeuvres83. During a manoeuvre what happens to the wing loading, explain your answer?

84. Normally a commercial aircraft will operate to load limits of +2.5g & -1.0g, however if an aircraft operator states load limits of +3.0g & -1.5g what will be the Ultimate Load Limit?

8.3 Theory Of Flight - Climbing85. An aircraft has a Climb angle & Weight component of 400 , Weight vector length of 8 & Drag Vector of 6. Draw out & calculate the Lift & Thrust components, what is the relationship between Lift & Weight?

86. What is the difference between the maximum angle of climb & the maximum rate of climb?

87. What is the max angle of climb governed by & state the fomulae?

88. What is the max rate of climb governed by & state the formulae?

89. Label the graph Axis below to indicate: Thrust Required, Thrust Available & Maximum Thrust Available. What type of aircraft is this performance data representative of?

90. For a Jet engine aircraft, what speed is normally used to provide the best engine efficiency?a. The Lowest TAS Velocityb. The Median TAS Velocityc. The Highest TAS Velocity

8.3 Theory Of Flight - Gliding91. An aircraft possesses a glide capability when the amount of ___________ available is _______ than the amount of _________ required to __________________________

92. What are the two components of an aircraft in a glide?

93. For an aircraft of a given weight, what will be the result in reducing the glide angle?a. An increase in drag, reducing the Lift/Drag Ratiob. A decrease in Drag, increasing the Lift/Drag Ratioc. No change to the Lift/Drag Ratio

94. An aircrafts glide distance is 3nm, with a reduction in altitude of 0.5nm. What is the aircrafts Lift/Drag Ratio?

95. An aircrafts V(IMD) is 85Knots. If the airspeed in the glide is adjusted to 70knots & 95Knots respectively, which speed will the aircraft achieve the further ground distance? Explain your answer.

96. Where can the best glide angle and weight adjustment be found for an aircraft & what effect will an increase in weight have on the Glide endurance & Range?

8.3 Theory Of Flight - Turning97. For an aircraft in a turn, which components provides the Centripetal force and support for the weight of the aircraft?

98. An aircraft enters a turn clock-wise, explain what actions must be carried out by the pilot to maintain level flight? Explain your answer.

99. The factors that are affected with a change in aircraft weight are _______ _______ & ________ radius ___ _________ __ ________.100. For an aircraft with a fixed vector of lift in a turn, if the weight of the aircraft is doubled, what will happen to the available Load Factor?

101. An aircraft with an All Up Weight of 25,000kg enters a turn at an angle of 300 what will be the required lift and resulting g loading?

102. What are the three conditions that must be me for the minimum radius of turn?

I.

II.

103. An aircraft weighs 100,000lbs, a wing area of 100 ft sq & structural limit of 300,000lbs. Calculate:

I. Wing Loading

II. Load Factor

104. Will a heavier aircraft than in question above be able to achieve a greater or lower bank angle? Explain your answer.

105. State the radius of turn formulae and the relationship with weight & Speed?

106. As altitude increases, the rate of turn and minimum turn radius:a. Decreasesb. Increasesc. Remain the same.

8.3 Theory Of Flight Lift Augmentation107. Leading edge devices, cause the velocity of airflow over the wing to ________, which in turn delays the ________ _________, allowing the __________ ____ ___________ to move forward. This _______________ the stalling Angle __ _________, which effectively ______________ the lift at ___________ airspeeds.108. Complete the table below (drawing the device in the Type column) for the characteristics of the Augmentation devices, listing advantages/disadvantages:TypeLeading Edge Device EffectTypeTrailing Edge Device Effect

Slats

Plain

Flaps

Split

DroopedExtension

Krueger

Combination

109. Look at the graph below, label the axis and match each lift profile to the High Lift Device configuration: Plain Aerofoil, Aerofoil with Flaps, Aerofoil with Flaps & Slats.

110. From the plotted characteristics in the graph above, what are the aerodynamic cross-sections of the Aerofoils?

8.4 Flight Stability & Dynamics - Introduction111. Roll is motion about the _______________ Axis & provides stability in the _________axis. Pitch is motion about the _______________ Axis & provides stability in the _________axis. Yaw is motion about the _______________ Axis & provides stability in the _________axis. 112. Stability characteristics of an aircraft are determined by:

a. The pilots control inputb. The design of the aircraftc. Weather conditions during the flight

113. What is the relationship between stability & controllability for an aircraft?

114. An aircraft reacts to aerodynamic disturbances but what defines (or is the difference) between Dynamic & Static Stability.

8.4 Flight Stability & Dynamics Static & Dynamic Stability115. Provide three examples of Static Stability & whether it is Positive, Neutral or Negative stability:

I. PositiveII. NeutralIII. Negative

116. Which type of dynamic stability can be said to be the opposite of Dynamic Unstable (Divergent Oscillation)? Draw the plotted chart of the flight path.

117. What is Dead Beat Stability? Draw the plotted chart of the Flight Path.

118. If a gust of wind forces an aircraft into a nose down attitude, what effective force is being provided by the Tail-plane to counteract this?

a. Lift on the lower part of the tail-plane providing an effective downward forceb. Lift on the upper part of the tail-plane providing an effective upward forcec. No reaction forces will be provided by the tail-plane.

119. What is the degree of longitudinal stability of an aircraft dependant on? Explain your answers.

120. If the C of G for an aircraft is moved to the aft C of G point, this will result in reduced __________, meaning that the stick-force required to move the flying control surface is _____________.121. Where are most aircraft range of movement of C Of G, what is it called & where can the information for each aircraft type be found?

122. What are the three factors determining the Coefficient of Lift (CL) for a Tail?

123. The size of the __________ arm multiplied by the ____________ area is known as the ____________ ______________ & is one of the main parameters designers use in determining the __________ of the ___________ required. 124. For an aircraft to maintain stability in flight, the tail-plane CW _____________ force OR _______________(LT), should equal the main-plane ACW __________ force OR _________________ (LW).125. For an aircraft to have stability, if the main-plane Lift is 6 units acting through the wings Centre of Pressure (C of P), 2 Units away from the C of G & the tail provides a download of 2 Units, through its C of P. How long is the tail-plane C of P from the C of G?

126. What is the Longitudinal Dihedral Angle?

a. The difference in the Angle of incidence between the main-plane & tail-plane, which is measured between the RAF & Chord-lines of both surfaces.b. The difference in the Angle of Attack between the main-plane & tail-plane, which is measured between the RAF & Chord-lines of the main-plane and tail-plane.c. The difference in the Angle of Incidence between the main-plane & tail-plane, which is measured between Chord-lines of the main-plane and tail-plane.

127. Identify a further three factors affecting stability and explain the one of them.I.

II.

III.

8.4 Directional Stability128. What provides directional stability for an aircraft & what two factors determine the degree of directional stability?

129. Where is the moment arm measured for the Vertical stabiliser on an aircraft?

130. A high speed aircrafts vertical stabiliser can stall, due to wind gusts, how can designers rectify this problem?

a. Fit larger vertical stabilisersb. Fit smaller vertical stabilisers with large ARc. Build in more sweep-back into the vertical stabiliser

131. The lateral stability of an aircraft is the ability of an aircraft to recover from a __________naturally about its _____________ axis.