Statistics for PRINCIPLES OF FLIGHT 080

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Answer Stats

Question	Answer	% Correct
An aeroplane wing stalls when:	The critical angle of attack is exceeded.	80%
If the indicated air speed of an aircraft is increased from 50 kts to 100 kts, parasite drag will be	Four times greater.	70%
An aircraft rotates about:	Its centre of gravity.	69%
Yawing is movement around the ____ axis.	Normal.	65%
The symbol for dynamic pressure is:	Q	64%
An aeroplane which is inherently stable will:	Have a built-in tendency to return to its original state following the removal of any disturbing force.	63%
Which wing shape has the greatest induced drag?	Rectangular.	63%
What is the load factor in a 60° banked level turn? (See LAPL/PPL 080-01)	2.0 G	57%
If the velocity of an airstream is doubled the drag coefficient will:	Increase 4-times	56%
Assuming that the pressure at sea level is ISA, but the temperature is 10 C higher than ISA, the density will be:	Less than ISA.	54%
When the aircraft is in a spin, the direction of spin is most reliably found by reference to which of the following indications?	Turn needle	53%
An aircraft's rudder is fitted with a balance tab. Movement of the rudder bar to the right, to yaw the aircraft to the right, will move the balance tab to the:	Left and the rudder to the right.	48%
A pilot lowers the flaps while keeping the airspeed constant. In order to maintain level flight, the angle of attack:	Must be reduced.	47%
If the angle of attack and other factors remain constant, and the airspeed is doubled, lift will be:	Quadrupled.	47%
The stalling speed of an aircraft in straight and level flight is 60 kt, lAS. What is its stalling speed in a level 60° banked turn?	85 kt.	46%
Dynamic pressure may be expressed by the formula:	Q = 1/2pV².	46%
Air pressure:	Acts in all directions.	45%
As indicated air speed (lAS) is reduced, in order to maintain altitude, the pilot must:	Increase the angle of attack to maintain the correct lift force.	45%
If the control column is moved to the right, a balance tab on the left aileron should:	Move up relative to the aileron.	45%
An aircraft is disturbed from its flight path by a gust of wind. If it tends to return to its original flight path without pilot intervention, the aircraft is said to possess:	Positive Dynamic Stability.	45%
The purpose of a trim tab is:	To zero the load on the pilots controls in the flight attitude required.	45%
The maximum speed at which the aircraft can be flown with flaps extended is called:	VFE	45%
Density:	Reduces with altitude increase.	44%
The tendency of an aircraft to develop forces which restore it to its original flight situation, when disturbed from a condition of steady flight, is known as:	Stability.	44%
If the control column is moved forward and to the left:	The left aileron moves up, right aileron moves down, elevator moves down.	44%
If in level flight the airspeed decreases below that for maximum lift/drag, the effect will be that:	Drag increases because of increased induced drag.	43%
When an aircraft is disturbed from its established flight path by, for example, turbulence, it is said to have positive stability if it subsequently:	Re-establishes its original flight path without any input from the pilot.	43%
If a landing is to be made without flaps the landing speed must be:	Increased	41%
The basic stalling speed of an aeroplane is 80 knots. In a level turn with 45° angle bank, the stalling speed is:	95 kt.	40%
The boundary layer consists of:	Laminar and turbulent flow area.	40%
If the angle of attack is increased above the stalling angle:	Lift will decrease and drag will increase.	40%
An aircraft is disturbed from its path by a gust of wind. Neutral stability is when, without pilot intervention, it:	Maintains the new path.	40%
Which of the four answer options most correctly completes the sentence? Increasing speed also increases lift because:	The increased speed of the air passing over an aerofoil's upper surface decreases the static pressure above the wing, thus creating a greater pressure differential across the upper and lower surface.	40%
Considering the forces acting upon an aeroplane, at constant airspeed, which statement is correct?	Weight always acts vertically downwards towards the centre of the Earth.	40%
An imaginary straight line running from the midpoint of the leading edge of an aerofoil to its trailing edge, is called the:	Chord	39%
The angle of attack is the angle between the:	Chord line and the relative airflow.	39%
That portion of the aircraft's total drag created by the production of lift is called:	Induced drag, which is greatly affected by changes in coefficient of lift and airspeed.	39%
The unit of force is the:	Newton.	39%
A typical stalling angle of attack for an aircraft wing is:	16°	38%
The smooth flow of air, where each molecule follows the path of the preceding molecule, is a definition of:	Laminar flow	38%
At a given indicated air speed, what effect will an increase in air density have on lift and drag?	Lift and drag will increase.	38%
The lateral axis of an aircraft is a line which:	Passes through the centre of gravity, parallel to a line through the wing tips.	38%
The definition of lift is:	The aerodynamic force which acts at 90° to the relative airflow.	38%
When considering the changes in density of the air with altitude, which of the following four options is correct?	The reduction in pressure with increasing altitude causes density to reduce.	38%
What is the significance of the speed known as VNO?	It signifies the upper limit of the normal operating speed range	37%
What must be the relationship between the forces acting on an aircraft in flight, for that aircraft to be in a state of equilibrium?	Lift must equal weight, and thrust must equal drag.	37%
Loading an aircraft so that the C of G exceeds the aft limits could result in:	Loss of longitudinal stability and the nose pitching up at slow speeds.	37%
The stalling speed of an aircraft, assuming weight to be constant, is a function of the:	Square root of the Load Factor	37%
If the cross sectional area of an airflow is mechanically reduced:	The mass flow remains constant and the velocity of the airflow increases.	37%
VNE is	The maximum airspeed at which the aircraft may be flown.	37%
The airspeed at which a pilot will not yet overstress the airframe of an aircraft by momentarily up-deflecting the elevator is:	VA	37%
The maximum value of the coefficient of lift is found at an angle of attack of approximately:	16 degrees	36%
The maximum allowable airspeed with flaps extended (VFE) is lower than cruising speed because:	At speeds higher than VFE the aerodynamic forces would overload the flap and wing structures.	36%
Lowering the flaps during a landing approach:	Increases the angle of descent without increasing the airspeed.	36%
The air pressure that acts on anything immersed in it:	Is also known as Static Pressure.	36%
In sub-sonic airflow, as air passes through a venturi, the mass flow ____ , the velocity ____ and the static pressure ____ .	Remains constant / increases then decreases / decreases then increases.	36%
Which flying control surface(s) give(s) control about the aircraft's normal axis?	The rudder	36%
In straight and level powered flight the following principal forces act on an aircraft:	Thrust, lift, drag, weight.	36%
When considering air: 1. Air has mass. 2. Air is not compressible. 3. Air is able to flow or change its shape when subject to even small pressures. 4. The viscosity of air is very high. 5. Moving air has kinetic energy.	1, 3 and 5.	35%
With a forward centre of gravity, an aircraft will have:	Decreased elevator effectiveness when flaring.	35%
If the Angle of Attack is increased beyond the Critical Angle of Attack, the wing will stall:	Regardless of airspeed or pitch attitude.	35%
What is the approximate percentage increase of a minimum speed if an aircraft mass is increased for 20%?	10%	34%
The critical angle of attack on the wing polar diagram is marked as: (See LAPL/PPL 080-02)	6	34%
The air flow over the wing's upper surface in straight and level flight, when compared with the airflow that is unaffected by the wing, will have:	A higher velocity.	34%
A wing which is inclined downwards from root to tip is said to have:	Anhedral	34%
The maximum value of the coefficient of lift is found:	At the stalling angle of attack.	34%
The reason for washout being designed into an aircraft wing is to:	Cause the inboard section of the wing to stall first.	34%
The presence of water vapour:	In air will reduce its density.	34%
Wing leading-edge devices such as slots, designed to allow flight at higher angles of attack, do so by:	Re-energising the airflow over the top of the wing, delaying separation.	34%
If the centre of gravity (C of G) of an aircraft is found to be within limits for take-off:	The C of G limits for landing must be checked, allowing for planned fuel consumption.	34%
If the velocity of an air mass is increased:	The kinetic energy will increase, the dynamic pressure will increase and the static pressure will decrease.	34%
The maximum gliding distance from 6.000 feet, for an aircraft in clean configuration, with a lift/drag ratio of 8:1, is approximately 8 nautical miles. If flaps are deployed:	The maximum gliding distance will be less.	34%
The purpose of a spring-bias trim system is	To reduce to zero the effort required by the pilot to counter stick force, after making a control movement.	34%
As airspeed increases, induced drag:	Decreases.	33%
At the stall, the Centre of Pressure moving backwards will cause the nose to ____, and the decreased lift will cause the aircraft to ____.	Drop / lose height	33%
A positively cambered aerofoil starts to produce lift at an angle of attack of approximately:	Minus 4 degrees.	33%
After a disturbance in pitch, an aircraft oscillates in pitch with increasing amplitude. It is:	Statically stable but dynamically unstable.	33%
Dynamic pressure equals:	Total pressure minus static pressure	33%
The angle of attack at which an aeroplane stalls:	Will remain constant, regardless of gross weight.	33%
Approximately for what percent will the stall speed increase if wing loading increases by 15%?	7%	32%
Which of the following four options describes the consequence of taking off with the manufacturer's recommended take-off flap setting selected?	A decrease in the length of the take-off run compared to a non-flap take-off.	32%
Fixed trim tabs on ailerons:	Can be adjusted on the ground after a test flight to make wings-level flight easier.	32%
Full flaps should be selected when:	Committed to land.	32%
In a climb at a steady speed, the thrust is:	Greater than the aerodynamic drag.	32%
When an aircraft is in a steady climb, the aerodynamic lift is ____ the weight.	Less than	32%
What is the maximum allowed bank angle when flying an aircraft with limiting load factor of +2,5 G? (See LAPL/PPL 080-01)	66°	31%
Controls are mass balanced in order to:	Eliminate control flutter	31%
The dynamic pressure exerted on an aircraft's frontal surface is equal to:	Half the density times the true airspeed squared.	31%
Stability around the normal axis:	Is increased if the keel surface behind the C of G is increased.	31%
Relative airflow is ____ and ____ the movement of the aircraft.	Parallel to / Opposite to	31%
When an aircraft is disturbed from its trimmed attitude by, for example, turbulence, it is said to have neutral stability if it subsequently:	Remains in the new attitude.	31%
The angle of climb is proportional to:	The amount by which the thrust exceeds the drag	31%
With the flaps lowered, the stalling speed will:	Decrease.	30%
As airspeed increases induced drag ____, parasite drag ____ and total drag ____.	Decreases / Increases / Decreases then increases.	30%
An aft centre of gravity will give:	Increased elevator effectiveness when flaring.	30%
Ailerons give:	Lateral control about the longitudinal axis	30%
In straight and level flight, the free stream airflow pressure, compared to that flowing under the wing, is:	Lower.	30%
Differential Ailerons' are a design feature that helps to counteract:	Adverse yaw.	29%
A control surface may be mass balanced by:	Attaching a weight acting forward of the hinge line.	29%
An aircraft wing is constructed with positive dihedral in order to give:	Lateral stability about the longitudinal axis.	29%
The primary and secondary effects of applying the left rudder alone are	Left yaw and left roll.	29%
A moving mass of air possesses kinetic energy. An object placed in the path of such a moving mass of air will be subject to:	Static pressure and dynamic pressure.	29%
Dynamic pressure is:	The amount of the total pressure by which the static pressure rises at a point where a moving airflow is brought completely to rest.	29%
When the control column is pushed forward, a balance tab on the elevator:	Will move up relative to the control surface.	29%
The maximum angle of climb of an aeroplane is determined by:	Excess engine thrust.	28%
Which of the answer options most correctly completes the sentence? The amount of lift a wing produces is directly proportional to:	The square root of the velocity of the air flowing over it	28%
By design, the centre of pressure on a particular aircraft remains behind the aircraft's C of G. If the aircraft is longitudinally stable and is displaced in pitch, nose down, by turbulence:	The tailplane will generate a downward force.	28%
When the C of G is close to the forward limit:	Very high stick forces are required to pitch because the aircraft is very stable.	28%
If an airplane weights 3.000 pounds, what approximate weight would the airplane structure be required to support during a 20° banked turn while maintaining altitude? (See LAPL/PPL 080-01)	3.180 lbs.	27%
If an airplane weights 4.600 pounds, what approximate weight would the airplane structure be required to support during a 50° banked turn while maintaining altitude? (See LAPL/PPL 080-01)	7.160 lbs	27%
What is the maximum allowed bank angle when flying an aircraft with limiting load factor of +3,8 G? (See LAPL/PPL 080-01)	75°	27%
On an aerofoil section, the force of lift acts perpendicular to, and the force of drag acts parallel to, the:	Chord line	27%
A control surface may have a mass balance fitted to it, in order to:	Help prevent a rapid and uncontrolled oscillation which is called "flutter".	27%
Following re-trimming for straight and level flight, in an aircraft with a C of G near its forward limit, and an elevator fitted with a conventional trim-tab:	Nose-up pitch authority will be reduced.	27%
Longitudinal stability is given:	The horizontal tailplane	27%
The purpose of an anti-balance tab is to:	Ensure that the pilot's physical control load increases with increase of control surface deflection.	26%
A high wing configuration with no dihedral, compared to a low wing configuration with no dihedral, will provide:	Greater lateral stability.	26%
Which flying control surface(s) give(s) longitudinal control?	The elevator.	26%
An aircraft has a tendency to fly right wing low with hands off. It is trimmed with a tab the left aileron. The trim tab will:	Move up causing the left wing to move down, ailerons remain neutral.	24%
If the aircraft weight is increased, without change of C of G position, the stalling angle attack will:	Remain the same.	24%
When flaps are lowered the stalling angle of attack of the wing	Decreases, but CLMAX increases.	23%
The part that gives most of the directional stability for an aircraft is:	The vertical fin.	23%
On an aircraft with a simple trim tab incorporated into a control surface, when the surface is moved, the tab remains in the same position relative to the:	Control surface.	22%
During a manoeuvre, the ailerons are deflected and returned to neutral when the aircraft has attained a small angle of bank. If the aircraft then returns to a wings- level attitude without further control movement, it is:	Statically stable but dynamically neutral.	22%
The angle of attack for a minimum drag on the wing polar diagram is marked as: (See LAPL/PPL 080-02)	3	21%
When displacing the ailerons from the neutral position:	The down-going aileron causes an increase in induced drag.	21%
If an aircraft is flown at its design manoeuvring speed VA:	It is possible to subject the aircraft to a load greater than its limit load during high 'g' manoeuvres.	20%
The phenomenon of flutter is described as:	Oscillatory motion of part or parts of the aircraft relative to the remainder of the structure.	19%
An aileron could be balanced aerodynamically by:	Having the control hinge set back behind the control surface leading edge	18%
At a constant angle of attack, a decrease in the airspeed of an aircraft will result in:	A decrease in lift and drag.	17%