The Three Axes of an Aircraft pass through The center of pressure The Centre Of Gravity The intersection of the centerlines of the fuselage and the wings.
The Chord Line is A line Equidistant from the upper and lower surfaces A straight line from leading edge to trailing edge A line tangential to the wing surface at the training edge.
In a symmetrical airfoil section, the mean camber line is A curve Coincident with the upper surface of the section A straight line coincident with the chord
.
The aspect ratio is The ratio between wing span and gross wing area The ratio between the square of the span and the mean chord The ration between the span and the mean chord.
An aircraft has a wingspan of 40 ft and a gross wing area of 200ft. The mean chord is 2 Ft 4 Ft 5 Ft.
The aspect ratio of the wing in Q5 is 5 8 20.
If an aircraft has a wing root that is laterally lower than it’s tip, it has
Anherdral Downwash Dihedral.
What control is affected by the elevators? Longitudinal control about the lateral axis Lateral control about the lateral axis Lateral control about the longitudinal axis.
What control is affected by the ailerons? Longitudinal control about the lateral axis Lateral control about the lateral axis Lateral control about the longitudinal axis.
When the aircraft is in straight and level flight, the normal axis is. Vertical Horizontal Lateral.
Directional control is achieved by use of the Elevator Ailerons Rudder.
A wing has a fineness ratio of 10% and a chord length of 30inches. The thickness would be. 10 inches 3 inches 0.3 inches.
The pressure at the stagnation point is equal to Total static pressure plus atmospheric pressure Atmospheric pressure plus absolute pressure Total dynamic pressure plus static pressure.
True Air Speed (TAS) is RAS corrected for compressibility IAS corrected for instrument and position error EAS corrected for density error.
Equivalent Air Speed (EAS) is TAS corrected for density error RAS corrected for compressibility RAS corrected for density error.
The drag of a smooth polished aerofoil section is low due to. A low induced drag A thicker boundary layer causing less skin friction A thinner and less turbulent boundary layer.
As an aircraft accelerates, the profile drag Decreases Increases Remains constant.
If an aerofoil is moving in airflow of constant speed, what effect will increase in angle of attack have on drag Drag will decrease Drag will increase Total drag will remain constant.
If the weight of an aircraft is increased, the profile drag for a given speed will. Increase Decrease Remain the same.
When the boundary layer changes from laminar flow to turbulent flow, it’s depth will Decrease Increase Remain the same.
Induced drag on an aerofoil section is caused by A rough surface The production of lift Skin friction.
The transition point on a wing is the point at which The airflow separates completely from the wing surface The boundary layer makes the transition from laminar flow to turbulent flow The total dynamic pressure and static pressure comes to a standstill.
If the weight of an aircraft flying at a given speed is increased Profile drag will decrease and induced drag will increase Profile drag and induced drag will increase Profile drag will remain unaffected and induced drag will increase.
As speed of an aircraft increases the induced drag Decrease in proportion (IAS) Increase in proportion to (IAS) Decrease in proportion to.
At minimum Drag speed (Vmd) Profile drag is greater than induced drag Profile drag is equal to induced drag Profile drag in less than induced drag.
The lift produced by a given speed is at a maximum At the optimum angle of attack When the angle of attack is zero At an angle of attack just before the stalling angle.
If the weight of an aircraft is increased, the maximum lift: drag ratio Will decrease Will not be affected Will increase.
The center of pressure is defined as The center of Gravity of the aircraft The point of maximum pressure on the under surface of the wing The point on the chord line through which the lift force acts.
If the angle of attack of an aerofoil section is increased the center of pressure will Move forward Move rearward Remain in the same position.
A symmetrical aerofoil section set at an angle of attack of zero to the airflow, will produce Negative lift Lift No lift.
If the airspeed over a wing, at a constant angle of attack, is trebled Lift will be increased four fold Lift will be increase nine fold Lift will be doubled.
The airflow over the top surface of an aerofoil will produce A smaller proportion of total lift than the airflow passing the over surface A greater proportion of total lift than the airflow passing the lower surface An equal proportion of total lift to that produced by the airflow passing the lower surface.
If air density is increased, the lift will Increase Decrease Remain the same.
All the factors that affect the lift produced by an aerofoil section are Angle of attack, air density, aerofoil shape, wing area, velocity Angle of attack, air temp., wing area, aerofoil shape, velocity Angle of attack, wing area, velocity, air density.
Vortices caused by induced drag are the result of: The airflow on the uppermost surface moving towards the tip, and the airflow on the lower surface moving towards the root The airflow on the lower surface moving towards the root, and the airflow on the upper surface moving towards the root The airflow on the upper surface moving towards the root and the airflow on the lower surface moving towards the tip.
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