AST Module 8 Full Set

The angle of attack of an aircrafts tailplane will influence its

When an aircraft is disturbed in pitch and its dynamic response is to continually move away from datum it has

To balance out variations in pitching moment due to movement of the center of pressure a

Longitudinal stability is about the

Stability in pitch

The horizontal stabilizer will help with

If an aircraft is displaced nose-up and the wing downwash angle is increased, the

Directional stability is achieved by controlling

The function of the vertical stabilizer is to promote directional stability about the

The function of the vertical stabilizer is to promote

Directional stability of an aircraft is determined by

The fin provides an aircraft with

The vertical stabilizer is considered a

An aircrafts keel surface aft of its C of G assists in providing

Lateral stability may be provided by the

Several factors affect the static lateral stability of an aircraft such as wing/fuselage interference. Others in the correct combination are

An aircraft constructed with dihedral will provide

A dihedral angle wing

On an aircraft with a dihedral wing, sideslip will produce a stable

If an aircraft has to much dihedral effect, it will tend to

To fly an aircraft straight and level at a low airspeed the aircraft must be flown with the wings

If an aircraft is flying at constant speed yet is descending then thrust

When a tail plane has to produce a down-load balancing force to maintain level flight at the same speed

In level flight, if a nose-down tendency occurs causing the tail plane to act as a down-load balance, the

An aircraft with a given weight, lift coefficient would be increased when

Two aircraft having the same lift drag ratio but with different weights start a glide from the same height

In a ‘power-on’ glide at a steady speed the thrust is

When an airplane stalls, the movement of center of pressure will cause the

To achieve maximum distance in a glide

In a steady rate climb, the

In a climb at steady speed the thrust is

An altitude known as service ceiling is when

Zooming for altitude will exchange

Power available for climb will be at its maximum when the

As the turn radius is reduced during a maneuver the load factor will

If an aircraft maintains a constant radius of turn but the speed is increased, the bank angle

An aircraft flying straight and level at a steady IAS begins a banked turn, to keep the IAS constant the engine power must

During a turn the lift force is resolved into

To achieve a minimum radius turn the maximum value of the product of lift coefficient and angle of attack must be obtained, plus the

As an aircraft pulls out of a dive, the load factor will be

Wing loading is the ratio of the

The ‘Rolling G limit’ will be

The relationship of forces on an aircraft is such that

The lift/weight turning moment of an aircraft is normally arranged to give a

When extension flap are deployed

When a trailing edge flap is in its landing position the wing lift is

The use of high lift devices on an airplanes wing during the landing phase of flight causes induced drag to

Deploying slotted extension flaps will

Operation of slats as lift augmentation devices is achieved

Leading edge slats will cause the transition point to move

The lift produced by an aero foil

The coefficient of lift

Lift coefficient may be increased by

A typical aero foil at zero degrees angle of attack will produce

The centre of pressure will move, over a cambered aero foil, in a normal working range aft of the leading edge by

If the weight of an aircraft is increased, the profile drag at a given speed will

Airflows mixing at airframe junctions will normally lead to

The induced drag of an aircraft is the drag due to the

One of the benefits of a ‘High Aspect Ratio’ wing is to reduce the

Zero lift drag will only occur when the aircraft is in

At the transition point the boundary layer becomes

The airflow over an aircraft wing of finite length is considered to be

Airflow around a cylindrical body becomes turbulent at the

The stagnation point on an aero foil is the point where the

Downstream from the leading edge of an aero foil, the boundary layer will

The layer of air extending from the surface of an object to the point where no dragging occurs is known as

The angle of attack of an aero foil is the angle that the

The chord line of an aero foil is

Wash out will ensure

Washout on a wing refers to

An aero foil with zero camber will

A common feature designed to prevent wing tip stall is

As the angle of attack increases

On an aero foil section, as the angle of attack is increased, the

When the angle of attack of an aero foil is increased

As an airflow approaches an aero foil at an angle of attack it experiences

On a rectangular wing platform a small stall strip is installed on the inboard section of the wings leading edge to ensure

If two identical aeroplane with a large difference in their weight are stalled

An aircraft wing is designed to stall

If the throttle is opened and the angle of attack is held constant, the airspeed and altitude are

When viewed from the rear, wingtip vortices rotate

What is the average value of the temperature lapse rate in the region of the Earths atmosphere known as the troposphere

The troposphere is a layer of the atmosphere where the temperature

Millibars are units of

Atmospheric pressure at any point is equal to

At the tropopause, air pressure is approximatel

The point in the atmosphere where air temperature stops reducing with increasing altitude and becomes constant is known as

Moisture in the air has the effect of

As the altitude increases, the viscosity of the air in the boundary layer will

The ISA standard for air density is

Assuming there is no change in temperature and pressure, the density of air

If pressure and temperature are known, air density may be calculated by using

The composition of air in the atmosphere is approximately

With increasing altitude, the air will

Aircraft normally operate in

The International standard atmosphere specifies

Air has weight and is compressible. It’s

The stratosphere lies

An aircraft flying at 10,000ft, compared to an aircraft of the same weight flying at the same IAS (Indicated Air Speed) but at sea level will have

As altitude increases, the local speed of sound will

To obtain accurate airspeed the

In order to calculate calibrated airspeed

Equivalent airspeed is calculated by multiplying calibrated airspeed by the ratio of

An indicated airspeed gauge must not have an error greater than

The ratio of ambient density to standard density when multiplied by

The troposphere is a layer of the atmosphere where the temperature

Pressure changes with change in volume (at constant temperature) so that it doubles when the volume

Millibars are units of

Density of the atmosphere will

The standard sea level pressure in the ISA is normally measured in millibars. Its metric equivalent in kilo-Pascal's is

Mach number is the ratio of the aircraft's

The angle of attack of an aero foil is the angle that the chord line makes with the

If the airspeed over a wing at a constant angle of attack is doubled, the lift will be

Aspect ratio is the ratio of aero foil

The optimum angle of an aero foil is that angle at which the

If the throttle is opened and the airspeed is held constant, the angle of attack is

The transition point on a wing is the point where the

If an aircraft is flying at constant speed then thrust is

The weight of an aircraft is considered to act at the center of

During a turn the lift force is resolved into two forces which are centripetal and a force equal and opposite to

A high L/D ratio

In a climb, the lift force is

During a glide the forces acting on an aircraft are

Stability about the lateral axis is given by the

Anhedral of a wing will

Pitch up in an aircraft is caused by

Dutch roll is

Increasing the size of the vertical stabilizer will

Moving the C of G aft will

Washout on a wing is when the incidence

The ISA value for air density is calculated by

Steady state airflow around a cylindrical body becomes turbulent at the

Airflow velocities around a body may be calculated using

The result of ice forming on an aero plane wing in flight will be, increase in weight and

According to Lapse Rate theory, if sea level temperature is 10’C temperature

Equivalent airspeed is calculated by multiplying calibrated airspeed by the ratio of

On a conventional aero foil section, as angle of attack is increased, the

Total drag on an aero plane in flight is greater than the sum of lift dependent drag, skin friction and form drag because of

To maintain the same altitude when velocity is increased

The most efficient angle of attack for an aero foil may be obtained by referring to the

The total drag of a symmetrical aero foil at zero angle of attack is made up of

When a aircraft in straight and level flight suffers an engine failure, the transition to a stable glide is due to the

In a stable climb, the rate of climb is proportional to the amount by which

When an aero plane is in a stable glide, if the pilot reduces the angle of attack, speed will

In a turn, if bank angle is increased, lift

In a turn during which a force of 2G is produced, the aero plane's stalling speed will be the

If two identical aero planes with a large difference in their weight are stalled

The lift generated by a general-purpose aero foil would be ‘zero’ at

Longitudinal dihedral is the angle between the

When an aero foil stalls, the movement of the center of pressure will cause the

The airflow pattern around an aircraft at low speed depends mainly on the

When an aircraft enters a rolling motion

An increase in the angle of attack on a symmetrical aero foil would cause the center of pressure to 

For an aircraft that has a positive angle of attack, the static pressure below the wing will normally be

The equation of continuity simply states that

Movement about the transverse axis effects 

Dynamic pressure is given by

The pressure co-efficient at the leading-edge stagnation point is

Stagnation pressure is given by

If the critical velocity of a flow becoming turbulent in a pipe of 1 inch is 20 fps, then the critical velocity in a 2 inch pipe would be

Viscosity of a gas is affected by changes in

The Reynolds number of a fluid flow, can be stated more easily as the measure of the ratio between the viscous forces and the

The greatest contribution to the lift of an aero foil comes from the

Static pressure on a asymmetrical aero foil would be greatest at the

The static margin of an aircraft is between the

On a cambered aero foil, the movement range of the center of pressure normally occurs between

On a asymmetrical wing a positive angle of attack in the normal operating range will cause the center of pressure to

On a lift curve the greatest part of the curve would be 

To prevent stall on a vertical stabilizer the

To increase the directional stability of an aircraft, the center of gravity is

The angle of attack where no lift is generated on a typical asymmetrical is

Leading edge vortex flow is normally found on 

On a 1/10 scale model, the mass is

Tail volume is given by the product of tail area time the 

Downwash from the mainplane has the effect of

In subsonic airflow air, is considered to be incompressible up to approximately

Aircraft that employ stick-free capability will have 

An aircraft that is designed with a large tail area allows for the center of gravity to be moved

Reynolds number effecting airflow properties depends upon

Increasing the wing dihedral of an aircraft will