Principles of Flight Test Astana

What happens to parasite drag if the true airspeed of an aircraft is multiplied by two, and all other parameters are kept constant? The parasite drag will?. Be divided by two. Be multiplied by two. Be divided by four. Be multiplied by four.

If the straight and level stall speed is 100 kt, what will be the stall speed in a 1.5g turn?. 81 kt. 100 kt. 122 kt. 150 kt.

If VS is 100 Id in straight and level flight, during a 45° bank turn VS wilt be: 80 kt. 100 kt. 140 kt. 119 kt.

The formula for lift is: L=rho V S CL. L = 1/2 rho V squared S CL. L = 2 rho V squared S CL. L = W.

The difference between IAS and TAS will: Remain constant at all times. Increase with decreasing temperature. Decrease with decreasing altitude. Increase with increasing density.

Which of the following is the most important result/problem caused by ice formation?. Increased weight. Reduction in CLMAX. Increased drag. Increased drag.

What phenomena causes induced drag?. The increased pressure at the leading edge. The spanwise flow, inward below the wing and outward above. Wing tip vortices. Wing tanks.

If the angle of attack is maintained constant, what happens to the coefficient of lift when flaps are deployed?. Decreases. Remains constant because angle of attack remains the same. Changes with the square of IAS. Increases.

The CG of an aeroplane is in a fixed position forward of the neutral point. Speed changes cause a departure from the trimmed position. Which of the following statements about the stick force stability is correct?. Increase of speed generates pull forces. Aeroplane nose-up trim decreases the stick force stability. Stick force stability is not affected by trim. An increase of 10 kt from the trimmed position at low speed has more effect on the stick force than an increase in 10 kt from the trimmed position at high speed.

High aspect ratio: Reduces induced drag. Increases maneuverability. Reduces parasite drag. Increases stalling speed.

For an aircraft flying straight and level at constant IAS, when flaps are deployed the induced drag: Decreases. Increases. Increases or decreases depending on the aircraft. Stays the same.

In accordance with Bernoulli’s Theorem, where PT = Total Pressure, PS = Static pressure and q = Dynamic pressure: PT-PS=q. PS+PT=q. PT=PS-q. PT+PS=q.

Which of the following statements about a venturi in a subsonic airflow is correct? (1) The dynamic pressure in the undisturbed flow and in the throat are equal. (2) The total pressure in the undisturbed flow and in the throat are equal. (1) and (2) are correct. (1) and (2) are incorrect. (1) is incorrect and (2) is correct. (1) is correct and (2) is incorrect.

In level flight at 1.4VS what is the approximate bank angle at which stall will occur?. 44 degrees. 30 degrees. 60 degrees. 32 degrees.

What is pitch angle?. The angle between the chord line and the horizontal plane. The angle between the chord line and the longitudinal axis. The angle between the longitudinal axis and the horizontal plane. The angle between the relative airflow and the longitudinal axis.

Stall speed in a turn is proportional to: The square root of the load factor. TAS squared. Lift. Weight.

What is load factor?. 1/Bank angle. Weight/ Wing area. Weight / Lift. Lift/ Weight.

An aircraft is flying straight and level, if density halves, aerodynamic drag will: Increase by a factor of four. Decrease by a factor of two. Increase by a factor of two. Decrease by a factor of four.

When considering the lift and drag forces on an aerofoil section: They are only normal to each other at one angle of attack. Drift is proportional to drag. They vary linearly. They both depend on the pressure distribution on the aerofoil section.

Vortex generators: Prevent spanwise flow. Use free stream flow to induce laminar flow. Use free stream flow to increase energy in the turbulent boundary layer. Take energy from the laminar flow to induce boundary layer separation.

When considering the Principle of Continuity for subsonic flow, what happens in a stream tube for a change in cross-sectional area?. RHO 1 = RHO 2. RHO2 > RHO. Cannot say without knowing the change in cross-sectional area of the stream tube. RHO 1 > RHO 2.

Which statement is correct?. The stick force per g can only be corrected by means of electronic devices (stability augmentation) in the case of an unacceptable value. If the slope of the fe-n line becomes negative, generally speaking this is not a problem for control of an aeroplane. The stick force per g increases when the CG is moved aft. The stick force per g must have both upper and lower limits in order to assure acceptable control characteristics.

Which of the following is used to activate a stall warning device?. Movement of the CG. Movement of the CP. Movement of the stagnation point. A reduction in dynamic pressure.

When considering the properties of a laminar and turbulent boundary layer, which of the following statements is correct?. Friction drag is the same. Separation point is most forward with a turbulent layer. Friction drag higher in turbulent. Friction drag higher in laminar.

Which of these statements about weight or mass is correct?. Mass = weight - volume. In the SI system the unit of measurement for weight is the kilogram. The weight of an object is independent of the acceleration due to gravity. The mass of an object is independent of the acceleration due to gravity.

Consider a uniform flow of air at velocity V in a stream tube. If the temperature of the air in the tube is raised: The mass flow will decrease and velocity V will remain constant. The mass flow remains constant and the velocity V will increase. The mass flow remains constant and velocity V decreases. The mass flow will increase and velocity V remain constant.

Which of the following is the cause of wing tip vortices?. Spanwise flow vector from the tip to the root on the bottom surface of the wing. Air spilling from the top surface to the bottom surface at the wing tip. Air spilling from the bottom surface to the top surface at the left wing tip and from the top surface to the bottom surface at the right wing tip. Air spilling from the bottom surface to the top surface at the wing tip.

Angle of attack is the angle between: Undisturbed airflow and mean camber tine. Undisturbed airflow and chord line. Local airflow and mean camber tine. Local airflow and chord line.

Compressibility effects depend on: EAS. TAS. Mach number. IAS.

Which of the following is the speed that would activate the stall warning?. 1.2VS. Above VS. 1.5VS. 1.15VS.

Static pressure acts: Parallel to dynamic pressure. In all directions. Downwards. Parallel to airflow.

Extending the flaps while maintaining a constant angle of attack (all other factors constant): The aircraft will yaw. The aircraft will roll. The aircraft will climb. The aircraft will sink suddenly.

What happens to the stall speed with flaps down, when compared to flaps up?. Decrease. Remain the same. Increase initially and decrease later. Increase.

If a jet aircraft is at 60 degrees bank angle during a constant altitude turn, the stall speed will be: 1.41 greater. 2.00 greater. 1.19 greater. 1.60 greater.

What does a stick pusher do?. Activate at a certain IAS and push the stick forward. Activate at a certain angle of attack and push the stick forward. Activate at a certain IAS and vibrate the stick. Activate at a certain angle of attack and pull the control column backwards.

As subsonic air flows through a convergent duct: (1) static pressure (2) velocity. (1) increases and (2) increases. (1) decreases and (2) decreases. (1) increases and (2) decreases. (1) decreases and (2) increases.

In order to maintain straight and level flight when trailing edge flaps are retracted, the angle of attack must: Be decreased. Be increased or decreased depending on type of flap. Stay the same because the lift requirement will be the same. Be increased.

With a swept wing the nose-up phenomena are caused by: Tip stall. Wing fences. Wing sweep prevents the nose-up phenomena. Deploying lift augmentation devices.

When the undercarriage is lowered in flight: Form drag will increase and the aircrafts nose-down pitching moment will be unchanged. Form drag will increase and the aircrafts nose-down pitching moment will increase. Induced drag will increase and the aircrafts nose-down pitching moment will increase. Induced drag will decrease and the aircrafts nose-down pitching moment will increase.

Which of the following is the correct designation of stall speed in the landing configuration?. VS1G. VSO. VS1. VSL.

A symmetrical aerofoil section at CL = 0 will produce?. A negative (nose-down) pitching moment. A positive (nose-up) pitching moment. Zero pitching moment. No aerodynamic force.

Which of the following decreases induced drag?. Anhedral. Wing fences. Low aspect ratio planform. Winglets.

Which of the following expressions is correct?. A=F x M. F=M x A. M=F x A. A=M/F.

True airspeed is: IAS corrected for instrument errors. CAS corrected for temperature and density. CAS corrected for wind. IAS corrected for wind.

A slat on an aerofoil: Increases the energy of the boundary layer and increases the maximum angle of attack. Deploys automatically under the influence of increased stagnation pressure at high angles of attack / low IAS. Increases the energy of the boundary layer and decreases the critical angle of attack. Increases the wing leading edge radius by rotating forward and down from its stowed position on the bottom side of the wing leading edge.

In a subsonic flow venturi, the relationship between the total pressure, static pressure and dynamic pressure of undisturbed air and air in the throat will be: (1) Dynamic pressure will be constant, static pressure will decrease. (2) Total pressure will be constant, dynamic pressure will increase. Both (1) and (2) are correct. (1) is correct and (2) is incorrect. (1) is incorrect and (2) is correct. Both (1) and (2) are incorrect.

Bernoulli’s Theorem states: Dynamic pressure increases and static pressure increases. Dynamic pressure increases and static pressure decreases. There is zero pressure at zero dynamic pressure. Dynamic pressure is maximum at stagnation point.

When considering the Principle of Continuity for incompressible subsonic flow, what happens in a stream tube with a change in cross-sectional area?. The density at the throat will be less than the density at the mouth. The density at the throat will be the same as the density at the mouth. Cannot say without knowing the change in cross-sectional area of the stream tube. The density at the throat will be greater than the density at the mouth.

A line from the centre of curvature of the leading edge to the trailing edge, equidistant from the top and bottom wing surface is the: Mean aerodynamic chord. Mean chord. Camber line. Upper camber line.

How is the pitching moment affected if flaps are deployed in straight and level flight?. Depends on CG position. Pitch up. Pitch down. Depends on CP position.

Which of the following aircraft designs would be most prone to super stall?. Pod mounted engines beneath the wing. Swept forward wing. Swept-back wing. T-tail.

Which statement about induced drag and tip vortices is correct?. On the upper surface there is a component of flow towards the root, whilst on the lower surface it is towards the tip. They both decrease at high angle of attack. Vortex generators diminish tip vortices. Row on upper and lower wing surfaces is towards the tip.

CDi is the ratio of?. (CL) squared to S. (CL) squared to AR. 1/2 rho V squared. 1/2 rho V squared S.

Which stall has the greatest angle of attack?. Deep stall. Accelerated stall. High speed stall (shock stall). Low speed stall.

The CP on a swept wing aircraft will move forward due to: Flow separation at the root due to spanwise flow. Boundary layer fences and spanwise flow. Change in wing angle of incidence. Tip stall of the wing.

Which of the following creates Lift?. An accelerated air mass. A retarded air mass. A symmetrical aerofoil at zero angle of attack in a high-speed flow. A change in direction of mass flow.

The lAS of a stall: May increase with increasing altitude, especially high altitude, forward CG and icing. Increases with high altitude, more flaps and slats. Altitude never affects stall speed IAS. Decreases with forward CG and increasing altitude.

Where does the lift act on the wing?. Centre of Pressure. Centre of Gravity. Always forward of the CG. Suction.

What causes a swept wing aircraft to pitch-up at the stall?. Rearward movement of the CP. Spanwise flow. Negative camber at the root. Separated airflow at the root.

What is a high speed stall?. Separation of the airflow due to shock wave formation. Excessive dynamic pressure causing airflow separation. A stall caused by increasing the load factor (g) during a maneuver. A stall due to decreasing CLMAX at speeds above M 0.4.

What effect on stall speed do the following have?. Increasing sweepback decreases stall speed. Increased anhedral increases stall speed. Decreasing sweep angle decreases stall speed. Fitting a T-tail will reduce stall speed.

On the approach to land, ground effect will begin to be felt at. When the angle of attack is increased. Upon elevator deflection. Half the wingspan above the ground. Twice the wingspan above the ground.

During which type of stall does the angle of attack have the smallest value?. Accelerated stall. Low speed stall. Deep stall. Shock stall.

What influence does the CG being on the forward limit have on VS and the stall angle?. VS decreases, stall angle remains constant. VS decreases, stall angle decreases. VS increases, stall angle remains constant. VS increases, stall angle increases.

Which of the following is the equation for power?. Pa/s squared. N/m. Kg/m/s squared. Nm/s.

When considering the coefficient of lift and angle of attack of aerofoil sections: A symmetrical section at zero angle of attack will produce a small positive coefficient of li. An asymmetrical section at zero angle of attack will produce zero coefficient of lift. Aerofoil section symmetry has no effect on lift coefficient. A symmetrical section at zero angle of attack will produce zero coefficient of lift.

Which of the following is the correct definition of aspect ratio?. Span divided by mean chord. Chord divided by span. measured at the 25% chord position. Chord divided by span. Span divided by tip chord.

As a smooth flow of subsonic air at a velocity less than M 0.4 flows through a divergent duct (i) static pressure (ii) velocity. (1) decreases and (2) decreases. (1) decreases and (2) increases. (1) increases and (2) increases. (1) increases and (2) decreases.

If IAS is doubled. by which of the following factors should the original CL be multiplied to maintain level flight?. 0.25. 0.5. 2.0. 4.0.

An aeroplane performs a right turn, the slip indicator is left of neutral. One way to co-ordinate the turn is to apply: More left rudder. More right rudder. Less left rudder. Less right bank.

The bank angle in a rate-one turn depends on: Load factor. Wind. TAS. Weight.

When considering an angle of attack versus coefficient of lift graph for a cambered aerofoil, where does the lift curve intersect the vertical CL axis?. Below the origin. At the point of origin. Above the origin. To the left of the origin.

Which of the following most accurately describes the airflow which causes wing tip vortices?. From the root to the tip on the top surface and from the tip to the root on the bottom surface over the wing tip. From the root to the tip on the top surface and from the tip to the root on the bottom surface over the trailing edge. From the tip to the root on the top surface and from the root to the tip on the bottom surface over the trailing edge. From the tip to the root on the top surface and from the root to the tip on the bottom surface over the wing tip.

As subsonic air flows through a convergent duct: (1) static pressure (2) velocity. (1) decreases and (2) decreases. (1) increases and (2) decreases. (1) decreases and (2) increases. (1) increases and (2) increases.

When in level flight at 1.3VS, what is the CL as a percentage of CLMAX?. 130%. 59%. 169%. 77%.

When flying straight and level in 1g flight, slightly below maximum all up weight, a basic stall warning system (flapper switch) activates at 75 kt IAS and the aircraft stalls at 68 kt IAS. Under the same conditions at maximum all up weight the margin between stall warning and stall will. Increase because increasing weight increases the 1g stall speed. Remain the same because increased weight increases the IAS that corresponds to a particular angle of attack. Decrease because increasing weight increases the 1g stall speed. Decrease because the 1g stall speed is an IAS.

Which of the following is the correct formula for drag?. 1/2 rho V squared AR CD S. 1/2 rho V squared CD S. 1/2 rho V squared CL S. 1/2 rho V (CL) squared S.

What causes deep stall in a swept-back wing?. Root stall. CP moves forward. CP moves aft. Spanwise flow from tip to root on wing upper surface.

On entering ground effect. Less thrust is required. Lift decreases. Ground effect has no effect on thrust required. More thrust is required.

The Principle of Continuity states that in a stream tube of decreasing cross-sectional area, the speed of a subsonic and incompressible airflow will: Sonic. Decrease. Remain the same. Increase.

At a constant IAS, induced drag is affected by: Aircraft weight. Wing location. Angle between chord line and longitudinal axis. Changes in thrust.

What is the cause of induced angle of attack?. The upward inclination of the free stream flow around the wing tips. Wing downwash altering the angle at which the airflow meets the tailplane. Downwash from trailing edge in the vicinity of the wing tips. Change in flow from effective angle of attack.

What is interference drag?. Drag due to the interaction of individual boundary layers at the junction of aircraft major components. Drag caused by high total pressure at the leading edges when compared to the lower pressure present at the trailing edge. Drag caused by the generation of lift. Airflow retardation over the aircraft structure due to surface irregularities.

Stalling speed increases when: The aircraft is subjected to minor altitude changes, i.e. 0 to 10000 ft. Flaps are deployed. Recovering from a steep dive. The aircraft weight decreases.

If flaps are extended in level flight: Lift and drag increase. CLMAX increases. CL increases. CL and drag increase.

What is the primary input for an artificial feel system?. Mach number. IAS. Static pressure. TAS.

CDi is proportional to which of the following?. CL. CL squared. CL MAX. The square root of the CL.

The formula for the Mach number is: M=LSS/TAS. M=TAS-LSS. M=TAS/LSS. M=IAS/LSS.

Considering the lift to drag ratio, in straight and level flight which of the following is correct?. LID is maximum when lift equals weight. L/D is maximum at the speed for minimum total drag. L/D maximum decreases with increasing lift. L/D is maximum when lift equals zero.

What is the effect of an aft shift of the CG on (1) static longitudinal stability and (2) the required control deflection for a given pitch change?. (1) increases (2) increases. (1) reduces (2) reduces. (1) increases (2) reduces. (1) reduces (2) increases.

Which of the following is a characteristic of laminar flow boundary layer?. No vortices. No flow normal to the surface. Constant temperature. Constant velocity.

At a constant CAS when flying below sea level an aircraft will have: A higher TAS than at sea level. A lower TAS than at sea level at ISA conditions. The same TAS, but an increased IAS. The same TAS as at sea level.

If the stalling speed in a 15° bank turn is 60 kt, what would the stall speed be in a 45° bank?. 60 kt. 83 kt. 70 kt. 85 kt.

Positive static longitudinal stability means: Nose-up moment when encountering an up gust. Nose-down pitching moment with a speed change at a constant angle of attack. Nose-up pitching moment with a speed change at a constant angle of attack. Nose-down pitching moment when encountering an up gust.

The effect of tropical rain on drag and stall speed would be to: Decrease drag and decrease stall speed. Increase drag and decrease stall speed. Increase drag and increase stall speed. Decrease drag and increase stall speed.

When compared to a laminar boundary layer: A turbulent boundary layer has more kinetic energy. A turbulent boundary layer is thinner. A turbulent boundary layer is more likely to separate. Less skin friction is generated by a turbulent layer.

What are the effects of tropical rain on: (1) CLMAX (2) Drag. (1) increase (2) increase. (1) decrease (2) increase. (1) decrease (2) decrease. (1) increase (2) decrease.

When considering the aerodynamic forces acting on an aerofoil section: Lift and drag increase linearly with an increase in angle of attack. Lift and drag act normal to each other only at one angle of attack. Lift increases linearly and drag increases exponentially with an increase in angle of attack. Lift and drag increase exponentially with an increase in angle of attack.

An aircraft has trailing edge flap positions of 0, 15, 30 and 45 degrees plus slats can be deployed. What will have the greatest negative influence on CL/ CD?. 0 - 15 flaps. Deploying slats. 15 - 30 flaps. 30 - 45 flaps.

After take-off why are the slats (if installed) always retracted later than the trailing edge flaps?. Because flaps extended gives a large decrease in stall speed with relatively less drag. Because slats extended gives a large decrease in stall speed with relatively less drag. Because VMCA with slats extended is more favourable compared to the flaps extended position. Because slats extended provides a better view from the cockpit than flaps extended.

A swept wing aircraft stalls and the wake contacts the horizontal tail. What would be the stall behavior?. Nose up. Nose up and/or elevator ineffectiveness. Tendency to increase speed after stall. Nose down.

The angle of attack at the stall: Increases with forward CG 3. Decreases with decrease in weight. Increases with aft CG. Is not affected by changes in weight.

A jet aircraft flying at high altitude encounters severe turbulence without encountering high speed buffet. If the aircraft decelerates, what type of stall could occur first?. Deep stall. Low speed stall. Shock stall. Accelerated stall.

In recovery from a spin: Ailerons are used to stop the spin. Airspeed increases. Ailerons should be kept neutral. Rudder and ailerons are used against the direction of spin rotation.

How does a plain flap increase CL?. Decreases the Aspect Ratio. Increases angle of attack. Increases camber. Changes position of CP.

Which of the following combination of characteristics would be most likely make an aircraft susceptible to deep stall?. Straight wing and a T-tail. Swept wing and wing mounted engines. Straight wing and wing mounted engines. Swept wing and a T-tail.

What are the units for wing loading and dynamic pressure?. N and N/square metre. Nm and Nm. N/square metre and N/square metre. N/square metre and joules.

The Principle of Continuity states that in a tube of increasing cross-sectional area, the speed of a subsonic and incompressible airflow will: Decrease. Sonic. Increase. Remain the same.

TAS is. Equal to IAS, multiplied by air density at sea level. Lower than the speed of the undisturbed airstream around the aircraft. Lower than IAS at ISA altitudes below sea level. Higher than the speed of the undisturbed airstream around the aircraft.

VS is 100 kt at n = 1. What will the stall speed be at n = 2. 200 kt. 119 kt. 100 kt. 141 kt.