The layer of atmosphere where temperature gradually falls

The lapse rate in the stratosphere region

The amount of air in the atmosphere apply ______ at the top surface

Which of the following flight operations is NOT dependent on density?

Density of air at sea level

Density is defined as

Temperature at sea level is

The portion of atmosphere below which layer changes in temperature take place

Coefficient of viscosity is defined as

The temperature variation near earth's surface

Viscosity coefficient

What are the flow properties considered in ISA?

ISA sea level temperature is

The property of air which makes all flight possible

Below which layer does temperature decrease rapidly?

Mean sea level pressure

What is the purpose of making ISA?

Aircraft performance's vital component

As altitude increases then

IAS includes

The portion of the atmosphere below the height at which the change occurs

Viscosity coefficient

The rate at which the pressure decreases is much ______ near the earth's surface than at altitude

For normal temperature

When some pressure is acted on any surface then what is actually acting?

In atmosphere, a mixture of gases nitrogen and oxygen in the proportion of approximately

Due to viscosity, wind velocity gradually ______ from the ground upwards

Pressure measuring instrument

Dynamic pressure is the

The mass of a cubic meter of air at ground level is roughly

Lapse rate at 1000 M is

Lapse rate at 1000 ft is

According to ISA, at sea level temperature, pressure & density

Fluid can be defined as

In static fluid

The characteristics of dry air at constant temperature & pressure

Ideal fluid or inviscid flow

Fluid is a substance

Pressure is a

The drag which is inversely proportional to square of velocity

Aileron provides which control

If an aircraft has infinite aspect ratio, then it will not be subjected to

The aileron control is used to provide control around

In streamline flow, the air

At high speed the induced drag

If the aspect ratio ______, the induced drag will be halved

The point at which laminar flow is changed to turbulent is

The increase of angle of incidence from root to tip

The angle between chord line and relative airflow is

The straight line from the leading edge of the wing to the trailing edge is called

The layer of air over the surface of an airfoil which is slower moving relative to the rest of airflow

If aspect ratio is higher, then induced drag is

If induced drag is to be reduced

MTCS – higher Reynolds number

On a delta wing aircraft, lift

Induced drag is a part of

The drag caused by the separation of the boundary layer

NACA 0009 airfoil is having

Factors of drag primarily depend on

Density is defined as

With greater aspect ratio, ______ will be reduced

Induced drag is not taken into consideration in

With greater aspect ratio, ______ will be reduced

When the AOA increases to the angle of maximum lift, this is known as

Rudder provides

An ideal airfoil has

Efficiency of airfoil is

The point of intersection of the resultant force line of the airfoil is called the

When flap will extend

Aileron gives ______ control

If center of gravity is forward of center of pressure, the nose of the aircraft will

The Newton's law of mechanics applicable to air

The point on a wing surface where the boundary layer starts

An airfoil stalls at

Mark the correct statement

Which of the following is profile drag?

The movement of center of pressure is independent from:

An ideal airfoil has:

Which control surface provides pitch control?

Induced drag is affected due to:

As long as you have lift, you have:

Law applicable for equilibrium flight is:

Elevator controls:

As AOA increases:

Lift of an aircraft is produced more due to:

Characteristics of airfoil depends on:

High thickness of the airfoil at the leading edge — what happens to the stall characteristics?

Reynolds number:

Movement of center of pressure is affected by:

When slat is extended the max CL of the aerofoil may be increased by as much as:

Angle of airfoil is slightly negative — will it generate lift?

At constant AOA, if density increases then L/D ratio:

Wave drag is generally produced at:

On a swept wing aircraft if both wing tips lose lift simultaneously the aircraft will:

The increase in kinetic energy due to increase in velocity is accompanied by a corresponding decrease in:

The geometric features of an airfoil section are:

Krueger flap is a:

Stagnation pressure:

The value of the dynamic pressure and hence the indicated speed at which this occurs will always be the _______ whatever the height.

Smooth surface encourages:

Airfoil with maximum camber well forward at leading edge will have _________ stall characteristics.

The streamline shapes which have given the least resistance at subsonic speeds have had a:

A laminar boundary layer over the whole surface of a wing — the skin friction would be reduced to about _________ of its value.

The turbulent layer has a much higher degree of shear at the surface and it is this which causes the skin friction to be much _________ than it is for the laminar boundary layer.

Drag coefficient of a body is dependent on:

In subsonic speed the air is:

In supersonic speed the air is:

The angle between the chord of the aerofoil and some fixed datum line in the aeroplane:

The upper surface by means of its decreased pressure provides:

The component that has hardly any effect on the position of the center of pressure:

In a flat plate, an increase of the angle of attack causes the center of pressure to move:

The pitching moment is positive when it tends to push the nose:

Relation between CL and AOA:

L/D ratio increases very rapidly up to about:

The L/D ratio increases very rapidly up to 3 or 4 degrees, at which angles the lift is nearly:

At subsonic speeds the aerodynamic center is usually about:

NACA 4412 is:

Aspect ratio for flight at subsonic speeds varies from:

While taking off, induced drag is:

When slat will extend:

Lines which show the direction of the flow of the fluid at any particular moment are called:

Speed of sound in gas is:

The camber convex of an airfoil on the upper surface is:

As velocity increases, the transition point on the wing will move:

The purpose of a slat is:

Fixed slat at high speed will give:

Camber & split flap will give:

Blown & jet flaps may be a serious disadvantage in the event of:

Reynolds number is the ratio of:

If Reynolds number is increasing, the flow will be:

If density is increasing, the Reynolds number will be:

If viscosity is increasing, the Reynolds number will be:

Airfoil with max camber well forward (say at 15% to 20% of the chord) may have:

There must be some point on the chord about which there is no change in pitching moment — this is called:

The concept of thrust is explained by:

Landing speed is ________ when flap & slat is open

When banking on a turn stalling speed is _________ than when landing

The increase in lift tends to _______ the glide angle

The steeper the original glide the greater the change in flight path involved and so the more speed must be there in hand for ______

After Flattening out we must lose any excess speed — this may be called _______

The gliding path is flatter so there is ________ change of path in flattening out

In straight and level flight when cruising power required curve and power available curve are perpendicular, it is

During turn the outer wing offers more

When engine failure occurs and lift is forward of the weight then

Higher weight in gliding flight is not affected by

During flat turn

In the case of aircraft nose drop, thrust line is placed ________ and drag line is ________

During turn stalling angle

During take-off before pulling off

Speed of sound at mean sea level

Performance capability of jet engine with propeller depends on

Performance capability of jet engine depends on

Landing speeds go up with _________ wing loading

A slight increase in the _________ to use for climbing

For equilibrium level flight

The airspeed during a spin is comparatively low and the rate of descent is also

Propeller converts _________ into _________

In straight and level flight we must prevent aircraft from

Rate of climb with respect to altitude

What changes an even and straight flight?

During gliding turn the aircraft rolls

Climb performance is related to

Except in special cases it is unadvisable to

During climbing turn the aircraft will roll

If we increase or decrease the best gliding speed, the flight path will

The speed of sound in water is roughly _________ times the speed of sound in air

Distance travelled by aircraft per unit fuel is

The weight of an aircraft is acting at which point

During climb which of the following curve should be considered?

In steeper turn, rudder position is taken by

If CP of an aircraft is behind CG, what happens to the nose?

During climbing

The flight Mach no. at which local supersonic flow first appears somewhere on the aircraft is

During takeoff, preferably aircraft will go

The ratio of Inertial to elastic force is called

Centre of drag is

The effects of an increase of altitude

At steady level flight, lift is equal to

During climbing turn, lift on the inner wing is

As weight of aircraft increases, lift has to be increased by increasing?

In an ordinary turn the inward centripetal force is provided by the aeroplane

Sharp leading edges are used in supersonic wings to reduce the

If we increase or decrease the best angle which gives L/D, the path of descent will be

If the aircraft glides along the wind the path of descent will be

Expansion wave in supersonic flow is a region where the speed will

If wing loading is increasing then stalling speed will be

The tail plane can produce lift in either +ve or –ve in order to produce the required moment for

At lower altitude power required is

Service Ceiling is the height at which rate of climb becomes

The aeroplane may travel upwards or downwards along the normal axis as in

The aeroplane may travel to right or left along the lateral axis — such motion is called

In climbing turn, the necessity for holding off bank is

Dutch roll

The propeller torque and engine torque will be exactly

The ratio of useful work given out by the propeller to the work put into it by the engine is

Movement of the center of gravity during flight caused, for instance, by

The angle of attack or the attitude of the aeroplane to the air is the same in level flight at all heights, provided the IAS

The less the total weight of the aircraft, the indicated airspeed will be

L/D is Maximum and drag will be

The angle of attack that gives the best L/D ratio will be the same at whatever the

The drag is the same at the same _________ at all heights

The higher we go, the greater is the _________ for the same

The higher we go, the greater is the TAS and therefore the greater the

To get maximum endurance we must use the

If the aircraft glides against the wind the path of descent will be

When banking on a turn the lift on the wings must be greater than the

The increase in drag tends to steepen the

Wherever the power available curve is _________ the power required curve, level flight is possible

The power available _________ with altitude

The power required _________ with altitude

TAS for the best rate of climb _________ with height

The greater the centripetal acceleration required, the higher will be the

Increase in velocity needs an ___________ in the angle of bank

The radius of the turn is increased, the angle of bank may be

Steep turns can only be accomplished if the engine is powerful enough to keep the aeroplane travelling at

Modern aircraft have a small side surface and if this is coupled with ________ directional stability

The radius of turn can be reduced as the angle of bank is _________

__________ is very rarely performed in practice

Maximum climb speed of aircraft

The ideal aeroplane must be one in which there is no ____

In the nature of a flying wing, we should obtain a lift

At high speed tight turn, radius of turn will be

Greater range if we fly a great deal faster than the

The tangent of the gliding angle is directly dependent on the

The greater the value of L/D the gliding angle will be

When banking on a turn the lift on the wings must be

The altitude at which required power and available power curves are tangential to each other is

In aerobatics every part of an aeroplane is given a load factor which varies, being usually

The angle of bank is quite independent of the ______

As the angle of bank increases, lift will

The normal duties of the engine are to propel the aeroplane at

A nose dive is really an exaggerated form of

In steep dive the weight is entirely balanced by

In gliding, ______ is rarely performed in practice

The aileron that also acts as a flap is known as

Differential movement of tail surface is known as

Low minimum speed and high maximum speed of aircraft will give

When the flap is lowered, the center of pressure on top of the surface will move

Streamlining will give

Estimating the power available from the engine and power required for level flight at various speeds is given by

The pilot can put the nose down slightly and maintain level flight at an

At any certain height the power available & power required curve touching each other is called

Lowering flaps during the glide will generally ________ the glide

During climb an increase in weight will mean a reduction in

The instrument used for measuring the flight Mach no. of an aircraft is ____________

The aircraft stopped rolling — the aerodynamic force will be influenced by

Aircraft take-off angle of attack during climbing

The aircraft stopped rolling — the aerodynamic force will be influenced by airstream passing over and below the aircraft

In the half way the stability and instability is called

Directional control is provided by

If the aircraft is in sideslip, which stability is affected?

The axis which passes from nose to tail is called

The normal axis which passes through

The position of CG which is too far back

The longitudinal stability depends upon

In all airplanes when flying at a small AOA, there is a resistance to roll on the down-going wing which will increase

Airplane which have a high tail plane on top of a high fin

When the controls are incorporated, ____________ will be activated

MTCS – about stability

Longitudinal stability is affected by

Longitudinal stability is highly affected due to

The control surfaces are placed as far as possible away from _________ so as to provide sufficient leverage to alter the position of the airplane

Longitudinal stability is affected by

If pitching moment about fuselage is disturbed, then which stability is affected?

If directional stability is too much and too little dihedral

Which of the following effects on stability?

More directional and less lateral stability

Trim tab requires

During a common method used to eliminate Dutch roll is by

Distribution of fuselage side surface more than ahead of CG than after will affect

The stability which is very rarely achieved in practice

Stick fixed condition

The longitudinal dihedral is made for

If the aircraft has a sweepback wing and stalls on the tip, the aircraft gives which movement?

Longitudinal stability is about which axis?

A small fin at the end of a long fuselage may be just as effective in producing

Aircraft will have weaker positive directional opposed to positive lateral stability can result in a

During equilibrium flight, operation stability depends on

The most common method of obtaining lateral stability is by use of

When an aircraft is in damping oscillation at a period of time

Longitudinal instability is due to the

Stick free condition

Lateral stability is about which axis?

Lateral stability is maintained by

If the planes are inclined upward towards the wing tips, the dihedral is

Lateral stability can be reduced by

Angle between main plane and tail plane is known as

The stability of an aircraft considered during design of the aircraft

If rudder pedal is un-operative, then which may be used?

The pendulum effect on a high wing aircraft

Which tab requires more stick force?

Forces & moments on the body caused by a disturbance that initially tends to return the body towards its equilibrium position

Modification of servo tab is called

Differential ailerons

In Slot-cum-aileron control, if aileron is moved down, the slat will

Adverse yaw will be counteracted by

The airflow crosses expansion wave, its velocity will

Mass Balancing will reduce

Degree of stability is affected by

If CG is low in a high wing aircraft

Mark the correct statement