Aerofoils The angle between relative airflow and the chord line is ?
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Aerofoils The angle of attack as in the case of a aircraft wing is defined as ?
Aerofoils For a fixed wing aircraft airplane or glider from straight and level flight to a steady horizontal turn lift must ?
Aerofoils for a fixed wing aircraft airplane or glider standard flight envelope flying at low speed means flying At large angle of attack, at small angle of attack, close to lowest drag angle of attack, close to zero lift angle of attack. 
Aerofoils for a fixed wing aircraft airplane or glider standard flight envelope flying at high speed means flying At small angle of attack, close to angle of attack max lift ot drag ratio, at large angle of attack, close to critical angle of attack. 
Aerofoils around a wing cross section aerodynamic lift generated At 75% due to reduced pressure on upper wing surface, at 25% due to reduced pressure on upper wing surface, at 25% due to increased pressure on upper wing surface, at 75% due to increased pressure on upper wing surface. 
Aerofoils all other factors of importance remaining constant when angle of attack increased The drag increases, the lift decreases, the lift increases but drag remains unaffected, the lift increases drag decreases. Question Section 7: Theory of flight 78 Answer 8
Stability the assistance control system stabilisation attitude altitude and guidance systems on a multi rotor aircraft done On board electronic, servo motors, actuators, electromagnets. Question Section 7: Theory of flight 78 Answer 9
Stability the movement of an aircraft about longitudinal axis known as Roll, yaw, pitch, a couple. Question Section 7: Theory of flight 78 Answer 10
Stability for a fixed wing aircraft airplane or glider manoeuvrability around lateral axis pitch Depends on load distribution, is greater when stability good, do not depend on load distribution, is tendency to return to original state of equilibrium after being disturbed. Question Section 7: Theory of flight 78 Answer 11
Stability for all fixed wing aircraft model you are able to change manoeuvrability onto lateral axis pitch acting on The center of gravity location, the aerodynamic centre location, centre of pressure location, the load factor. Question Section 7: Theory of flight 78 Answer 12
On a small fixed wing drone aircraft or glider forward displacement of centre of gravity will have effect of Increase stall speed, decrease stall speed, create a nose down attitude in level flight, create a nose up attitude in level flight. Question Section 7: Theory of flight 78 Answer 13
A fixed wing drone with a mass of 10 kg performing a co ordinated level turn at a bank angle of 60° it will have an equivalent weight of 2kg, 25 kg,5 kg, 3kg. Question Section 7: Theory of flight 78 Answer 14
Choose statement that best describes stability concept of an aircraft A stable aircraft tends to naturally resume its attitude after a disturbance, a stable aircraft very manoeuvrable requires dynamic compensation, an aircraft stable when forces acting on it are equal, a stable aircraft difficult to turn, climb or descent. Stability the inherent quality of an aircraft to correct conditions that may disturb its equilibrium, to return to or to continue on original flightpath. it primarily an aircraft design characteristic. the flightpaths attitudes an aircraft flies are limited the aerodynamic characteristics of aircraft, its propulsion system, its structural strength. these limitations indicate maximum performance maneuverability of aircraft. if aircraft to provide maximum utility, it must be safely controllable to full extent of these limits without exceeding pilot's strength or requiring exceptional flying ability. if an aircraft to fly straight steady along any arbitrary flightpath, forces acting on it must be in static equilibrium. the reaction of any body when its equilibrium disturbed referred to as stability. positive static stability initial tendency of aircraft to return to original state of equilibrium after being disturbed. Question Section 7: Theory of flight 78 Answer 15
The load factor on wings may be increased anytime The aircraft subjected to maneuvers other than straight level flight, centre of gravity (cg) shifted rearward to aft cg limit, gross weight reduced, aircraft turned off. In aerodynamics, maximum load factor (at given bank angle) a proportion between lift weight has a trigonometric relationship. the load factor measured in gs (acceleration of gravity), a unit of force equal to force exerted gravity on a body at rest indicates force to which a body subjected when it accelerated. any force applied to an aircraft to deflect its flight from a straight line produces a stress on its structure. the amount of this force the load factor. while a course in aerodynamics not a prerequisite obtaining a remote pilot certificate, competent pilot should have a solid understanding of forces that act on aircraft, advantageous use of these forces, the operating limitations of aircraft being flown. for example, a load factor of 3 means total load on an aircraft's structure three times its weight. since load factors are expressed in terms of gs, a load factor of 3 may be spoken of as 3 gs, or a load factor of 4 as 4 gs. with structural design of aircraft planned to withstand only a certain amount of overload, a knowledge of load factors has become essential all pilots. load factors are important two reasons 1. it possible a pilot to impose a dangerous overload on aircraft structures. 2. an increased load factor increases stalling speed makes stalls possible at seemingly safe flight speeds.
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