ppooff- giay 3

Multiple Choice

the force due to gravity is also know as

• weight

• lift

• drag

• thrust

Multiple Choice

the..............of an aircraft must remain within certain forward and aft limits, for reason of both stability and control

• centre of pressure

• centre of gravity

• aerodynamic centre

• neutral point

Multiple Choice

the acceleration of a body from a state of rest, or uniform motion in a straight line, is proportional to the applied force and inversely proportional to the mass. This statement is referred to as

• Newton 1st

• Newton 2st

• Newton 3st

• bernolli theorem

Multiple Choice

the SI unit of velocity

• m/s2

• m/s

• km/h

• knots

Multiple Choice

If air density decrease, the mass of air flowing over the aircraft in ta fiven time will

• increase

• increase then decrease

• decrease

• decrease then increase

Multiple Choice

Static pressure will exert the same force per square metre on

• the leading edge of an aerofoil

• the nose of aircraft

• the upper surface of an aerofoil

• all surface of an aeroplane

Multiple Choice

calculate the Mach number of an aircraft cruising at 32000 feet, with a TAS of 340 KTS and the outside air temprature of IAS -7*C

• 0.59

• 0.63

• 0.78

• 0.82

Multiple Choice

True airspeed is Calibrated Airspeed corrected for

• Position and instrument error

• Compressibility Error

• Density error

• Compressibility and density error

Multiple Choice

A streight line joining the centres of curvature of the leading edges of an aerofoil is known as

• Chord

• Camber Line

• Chord line

• Longitudinal Axis

Multiple Choice

As the AOA increase from -4*, the leading edge stagnation point moves from

• upper surface around the leading edge to the lower surface

• upper surface around the trailing edge to the lower surface

• lower surface around the leading edge to the upper surface

• lower surface around the trailing edge to the upper surface

Multiple Choice

The centre of Pressure is at......... just before the stall

• its most aft positon

• its most forward position

• its highest position

• its lowest position

Multiple Choice

A cruise speed is chosen so the aircraft operaties at its

• stalling AOA

• Critical AOA

• optimum AOA

• angle of incidence

Poll

the primary purpose of high lift device ( flap, slat, slot...) is to

• increase stalling speed

• increase take-off and landing distance

• reduce take-off and landing distance

• improve aerodynamic efficiency during cruise

Multiple Choice

The relationship between and indicated airspeed is such that

• parasite drag varies directly with the square of the indicated airspeed

• parasite drag varies inversely with the square of the indicated airspeed

• parasite drag varies directly with the indicated airspeed

• parasite drag is half of the indicated airspeed

Multiple Choice

Induce drag will be greater if

• the mass of the aircraft is heavier

• The surface area of the aircraft increase

• the speed of the aircraft increase

• the wingspan of the aircraft is greater

Multiple Choice

The speed at which total drag is at minimum(Vmd) occurs when

• Induce drag < parasite drag

• induce drag > parasite drag

• induce drag = parasite drag

• induce drag <= parasite drag

Multiple Choice

What happens when a pilot flies at speed slower than Vmd?

• The aircraft will enter a slow descend and the aircraft will acceleration

• there is a tendency for the aircraft to drift away from the trim speed and the aircraft is speed unstable

• Aircraft perfomance will improve during cruise

• the aircraft will begin

Multiple Choice

To recover from a stall or prevent a full stall

• the AOA must be decreased to reduce the adverse pressure gradient

• the engines must be advanced to full power

• Flaps should be extended to increase the wing surface areas

• the AOA must be increased to increase the adverse pressure gradient

Multiple Choice

Which of the following is not a sign of aircraft entering a stall?

• Buffeting of control

• Activation of stall warner

• Decreasing airspeed

• Increasing airspeed

Poll

The purpose of a stall strip is to:

• Improve aerodynamic effciency

• induce stalling of the wing root

• improve maximum range by reduce fuel burn

• Decrese induce drag

Multiple Choice

In flight icing usually accumulates at the leading edge of aerofoils and:

• Stall

• Buffeting

• Will severely increase surface roughness causing a significant decrease in CLmax

• Control Forces

Multiple Choice

The polar curve of an aerofoil is a graphic relation between:

• AOA and CL

• Cd and AOA

• TAS and stall speed

• Cl and Cd

Multiple Choice

A symmetrical aerofoil will

• Produce lift at negative AOA

• Produce zero lift at zero AOA

• produce lift at positive AOA

• product lift at any AOA

Multiple Choice

Symetrical aerofoils:

• have no camber because the chord line and camber line are coincidental

• Are commonly seen on most highspeed jet transport aircraft

• Are more aerodynamically efficient than asymmetrical aerofoils

• Have a lower stalling speed than asymmetrical aerofoils

Multiple Choice

Taper ratio is

• the ratio of root chord to tip chord

• the ratio of the tip chord to the root chord

• the ratio of the wing span to average chord

• the ratio of the wing span to the longitudinal axis

Multiple Choice

Wingtip vortices is most significant when

• an aircraft is equiped with wingtip fence

• an aircraft descend with idle thrust

• an aircraft with high aspect ratio flies at high speed

• an aircraft flies slowly and at higher angle of attack

Multiple Choice

a thinner wing

• Reduce fuel consumption

• reduce the stalling speed

• Does not require hight lift device to have an acceptable low minimum speed

• will generates less lift at a given angle of attack and have a higher minimum speed

Multiple Choice

the .......... increase with AOA up to maximum at about 4*

• L/D ratio

• CLmax

• Angle of incident

• Wing span

Multiple Choice

Vortex generators

• Add weight to the aircraft and therefore increase drag

• re-energise the low-energy boundary layer at the surface of a wing

• restrict the outward flow of the boundary layer

• Makes the aircraft wings look more pleasant

Multiple Choice

A subsonic airflow through a convergent duct

i: static pressure

ii: velocity

• i: decrease

  ii: increase

• i: increase

  ii: increase

• i: decrease

  ii: decrease

• i: increase

  ii: decrease

Multiple Choice

the maximum lift/drag ratio (L/Dmax) of a given aerofoil section will occur

• at one specific angle of attack

• at the best angle of attack

• at the best climb gradient

• at zero angle of attack

Multiple Choice

if TAS is constant, to maintain straight and level flight with reduced air density the angle of attack of an aircraft wing must be

• Decrease

• Increase

• Unaltered

• Increased the critical angle of attack

Multiple Choice

Calibrated airspeed is indicated airspeed corrected for:

• Position and Density Errors

• Position and instrument Errors

• Compressibility Errors

• Density Errors

Multiple Choice

To maintain the required Lift force, if density decrease:

• the aircraft must climb to a higher altitude

• The speed of the aircraft through the air must be increase

• The speed of the aircraft through the air must be decrease

• the outside air temperature must be lowered to increase density

Multiple Choice

A heavier aircraft

• Will stall at a lower AOA

• is normally more fuel efficient

• will have a slower stalling speed

• will have a higher Vmd

Multiple Choice

From the leading edge, the correct sequence of airflow is

• Laminar flow,transition, turbulent flow,separation

• Laminar flow,turbulent flow,transition, separation

• laminar flow, transition, separation, turbulance flow

• laminar flow, separation, transition, turbulance flow

Multiple Choice

During climb at a constant CAS, the Mach number will

• Remain constant

• Increase

• increase initially and remain constant subsequently

• decrease initially and increase subsequently

Multiple Choice

interference drag is result of:

• Downwash behind the wing

• Aerodynamic interaction between aeroplane parts

• separation of the induced vortex

• The addition of induced and parasite drag

Multiple Choice

Aircraft with very high aspect ratio wings will experience:

• improved ground clearance in roll during take-off and landing

• increased induced drag from greater wingtip vortices

• excessive wing bending moments

• higher airspeed from greater lift generated from the wings

Multiple Choice

the (subsonic) static pressure

• is the total pressure plus the dynamic pressure

• increase in a flow in a tube when the diameter decrease

• is the pressure in a point at which the velocity has become zero

• decrease in a flow in a tube when the diameter decrease