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Aircraft Systems Quiz: Flight Controls, High-Lift Devices, and Stalls, Exams of Aviation

A series of multiple-choice questions and answers covering key concepts in aerodynamics and aircraft systems. It delves into the functions of primary and auxiliary flight controls, high-lift devices, stall characteristics, and the impact of various factors on aircraft performance. The questions provide a comprehensive overview of these essential topics, making it a valuable resource for students and professionals in aviation.

Typology: Exams

2024/2025

Available from 02/03/2025

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ADX: SECTION 10 (AERODYNAMICS
&AIRCRAFT SYSTEM) 99 Quiz
Questions Well Answered
Which of the following is considered a primary flight control? - โœ” โœ” Elevator
Which of the following is considered an auxiliary flight control? - โœ” โœ” Leading-edge flaps.
What is the purpose of a control tab? - โœ” โœ” Move the flight controls in the event of manual
reversion.
What is the purpose of an elevator trim tab? - โœ” โœ” Modify the downward tail load for various
airspeeds in flight eliminating flight-control pressures.
Which of the following are considered primary flight controls? - โœ” โœ” Outboard ailerons.
Which is a purpose of leading-edge flaps? - โœ” โœ” Increase the camber of the wing.
What is a purpose of flight spoilers? - โœ” โœ” Reduce lift without increasing airspeed.
For which purpose may flight spoilers be used? - โœ” โœ” Reduce the wings' lift upon landing.
Which is a purpose of ground spoilers? - โœ” โœ” Reduce the wings' lift upon landing.
The primary purpose of high-lift devices is to increase the - โœ” โœ” lift at low speeds.
What is the primary function of the leading edge flaps in landing configuration during the flare before
touchdown? - โœ” โœ” Prevent flow separation.
What effect does the leading edge slot in the wing have on performance - โœ” โœ” Changes the stalling
angle of attack to a higher angle
On which type of wing are flaps most effective? - โœ” โœ” Thick wing
When compared to plain flaps, split flaps - โœ” โœ” produce only slightly more lift, but much more drag.
Fowler flaps as compared to split flaps - โœ” โœ” generate more nose down pitching moment.
Upon landing, spoilers - โœ” โœ” function by increasing ground to tire friction.
One method of boundary layer control is accomplished by injecting - โœ” โœ” a jet of air into the leading
edge to energize the boundary layer.
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ADX: SECTION 10 (AERODYNAMICS

&AIRCRAFT SYSTEM) 99 Quiz

Questions Well Answered

Which of the following is considered a primary flight control? - โœ” โœ” Elevator Which of the following is considered an auxiliary flight control? - โœ” โœ” Leading-edge flaps. What is the purpose of a control tab? - โœ” โœ” Move the flight controls in the event of manual reversion. What is the purpose of an elevator trim tab? - โœ” โœ” Modify the downward tail load for various airspeeds in flight eliminating flight-control pressures. Which of the following are considered primary flight controls? - โœ” โœ” Outboard ailerons. Which is a purpose of leading-edge flaps? - โœ” โœ” Increase the camber of the wing. What is a purpose of flight spoilers? - โœ” โœ” Reduce lift without increasing airspeed. For which purpose may flight spoilers be used? - โœ” โœ” Reduce the wings' lift upon landing. Which is a purpose of ground spoilers? - โœ” โœ” Reduce the wings' lift upon landing. The primary purpose of high-lift devices is to increase the - โœ” โœ” lift at low speeds. What is the primary function of the leading edge flaps in landing configuration during the flare before touchdown? - โœ” โœ” Prevent flow separation. What effect does the leading edge slot in the wing have on performance - โœ” โœ” Changes the stalling angle of attack to a higher angle On which type of wing are flaps most effective? - โœ” โœ” Thick wing When compared to plain flaps, split flaps - โœ” โœ” produce only slightly more lift, but much more drag. Fowler flaps as compared to split flaps - โœ” โœ” generate more nose down pitching moment. Upon landing, spoilers - โœ” โœ” function by increasing ground to tire friction. One method of boundary layer control is accomplished by injecting - โœ” โœ” a jet of air into the leading edge to energize the boundary layer.

On most airplanes, the first 50% of flap deflection causes - โœ” โœ” more than 50% of the total change in lift Compared to a straight wing, swept wing flaps are - โœ” โœ” less effective. What is the relationship between induced and parasite drag when the gross weight is increased? - โœ” โœ” Induced drag increases more than parasite drag. In a jet powered airplane (fan or pure jet) the angle of attack at stall is - โœ” โœ” essentially the same power on or power off. An increase in airspeed above the stall speed will require - โœ” โœ” a corresponding decrease in angle of attack and coefficient of lift. Lift coefficient must be maximum at the - โœ” โœ” airplane stall speed. When at high angle of attack the boundary layer tends to - โœ” โœ” loop around the upper camber line. An airplane flying at L/DMAX will have - โœ” โœ” the same glide performance at all weights. Any angle of attack lower or higher than L/DMAX - โœ” โœ” increases total drag. Which is a purpose of wing-mounted vortex generators? - โœ” โœ” Reduce the drag caused by supersonic flow over portions of the wing. Which is a purpose of wing-mounted vortex generators? - โœ” โœ” Delays the onset of drag divergence at high speeds and aids in maintaining aileron effectiveness at high speeds. Airflow separation over the wing can be delayed by using vortex generators, - โœ” โœ” making the wing surface rough and/or directing high pressure air over the top of the wing or flap through slots. If the boundary layer separates - โœ” โœ” the wing is about to stall and stop producing lift. How does Vs (KTAS) change with altitude? - โœ” โœ” varies directly with altitude. Stall warning devices must sense - โœ” โœ” pressure distribution. An airplane stall warning device must sense - โœ” โœ” relative wind. An aircraft in a steady state, constant altitude turn - โœ” โœ” experiences higher stall speeds. Fundamental recovery from a stall requires - โœ” โœ” decreasing the angle of attack The stall speed of an airplane - โœ” โœ” is affected by weight and bank angle. What is load factor? - โœ” โœ” Lift divided by the total weight.

What is the result of a shock-induced separation of airflow occurring symmetrically near the wing root of a sweptwing aircraft? - โœ” โœ” A severe moment or "Mach tuck." What is one disadvantage of a sweptwing design? - โœ” โœ” The wingtip section stalls prior to the wing root. What is the condition known as when gusts cause a swept wing type airplane to roll in one direction while yawing in the other? - โœ” โœ” Dutch roll. What is the movement of the center of pressure when the wingtips of a sweptwing airplane are shock- stalled first? - โœ” โœ” Inward and forward Swept wings causes a significant - โœ” โœ” reduction in effectiveness of flaps. Free directional oscillation (dutch roll) is - โœ” โœ” a coupled lateral/directional oscillation, that is usually dynamically stable. A jet airplane operating at a cruise speed of .75 Mach with outside air temperature of -42หšC has a true airspeed of - โœ” โœ” 446 knots. A definition of the term "viscous hydroplaning" is where - โœ” โœ” a film of moisture covers the painted or rubber-coated portion of the runway. Which term describes the hydroplaning which occurs when an airplane's tire is effectively held off a smooth runway surface by steam generated by friction? - โœ” โœ” Reverted rubber hydroplaning. At what minimum speed (rounded off) could dynamic hydroplaning occur on main tires having a pressure of 121 PSI? - โœ” โœ” 96 knots. At what minimum speed will dynamic hydroplaning begin if a tire has an air pressure of 70 PSI? - โœ” โœ” 75 knots. What is the best method of speed reduction if hydroplaning is experienced on landing? - โœ” โœ” Apply aerodynamic braking to the fullest advantage. Compared to dynamic hydroplaning, at what speed does viscous hydroplaning occur when landing on a smooth, wet runway? - โœ” โœ” At a lower speed than dynamic hydroplaning. What effect, if any, will landing at a higher-than-recommended touchdown speed have on hydroplaning? - โœ” โœ” Increases hydroplaning potential regardless of braking. How should thrust reversers be applied to reduce landing distance for turbojet aircraft? - โœ” โœ” Immediately after ground contact.

How should reverse thrust propellers be used during landing for maximum effectiveness in stopping? - โœ” โœ” Use maximum reverse power as soon as possible after touchdown. Upon landing, thrust reversers - โœ” โœ” should be deployed as soon as the nose wheel is in firm contact with the runway. Which is an effect of ice, snow, or frost formation on an airplane? - โœ” โœ” Decreased angle of attack for stalls. Which is a disadvantage of the one-step over the two-step process when deicing/anti-icing an airplane?

  • โœ” โœ” More fluid is used with the one-step method when large deposits of ice and snow must be flushed off airplane surfaces. The purpose of diluting ethylene glycol deicing fluid with water in nonprecipitation conditions is to - โœ” โœ” decrease the freeze point. Which procedure increases holding time when deicing/anti-icing an airplane using a two-step process? - โœ” โœ” Heated Type 1 fluid followed by cold Type 2 fluid. Which of the following will decrease the holding time during anti-icing using a two-step process? - โœ” โœ” Apply heated Type 2 fluid. What should the deice/anti-ice fluid temperature be during the last step of a two-phase process? - โœ” โœ” Cold. What is the minimum glycol content of Type 1 deicing/anti-icing fluid? - โœ” โœ” 80 percent. What is the minimum glycol content of Type 2 deicing/anti-icing fluid? - โœ” โœ” 50 percent. Anti-icing fluid should provide freezing point protection to - โœ” โœ” a freezing point no greater than 20ยฐF below the ambient or airplane surface temperature Which is an effect of ice, snow, or frost formation on an airplane? - โœ” โœ” Increased stall speed. Freezing Point Depressant (FPD) fluids used for deicing - โœ” โœ” are intended to provide ice protection on the ground only. Test data indicate that ice, snow, or frost having a thickness and roughness similar to medium or coarse sandpaper on the leading edge and upper surface of a wing can - โœ” โœ” reduce lift by as much as 30 percent and increase drag by 40 percent. Snow on top of deicing or anti-icing fluids - โœ” โœ” must be considered as adhering to the aircraft. Freezing Point Depressant (FPD) fluids are highly soluble in water;