Free for a few more days!
Sign up to unlock all our services and 1230 corrected and explained questions.

Question 78-1 : Aerofoils at constant speed if angle of attack of a fixed wing airplane is increased ? [ Procedure DJI ]

Lift increases until the critical angle of attack is exceed then lift decreases

Question 78-2 : Aerofoils the angle between relative airflow and the chord line is ?

The angle of attack.

exemple 82: The angle of attack
The pitch angle. the descent path angle. the climb path angle.

Question 78-3 : Aerofoils the angle of attack as in the case of a aircraft wing is defined as ?

The angle between the chord line and relative airflow.

exemple 86: The angle between the chord line and relative airflow
Relative airflow and the horizontal plane. the chord line and the horizontal plane. longitudinal axis and the horizontal plane.

Question 78-4 : Aerofoils for a fixed wing aircraft airplane or glider from straight and level flight to a steady horizontal turn lift must ?

Increase.

exemple 90: Increase
First decrease and after increase. decrease. remain unchanged.

Question 78-5 : Aerofoils for a fixed wing aircraft airplane or glider for standard flight envelope flying at low speed means flying ?

At large angle of attack.

exemple 94: At large angle of attack
At small angle of attack. close to the lowest drag angle of attack. close to the zero lift angle of attack.

Question 78-6 : Aerofoils for a fixed wing aircraft airplane or glider for standard flight envelope flying at high speed means flying ?

At small angle of attack.

exemple 98: At small angle of attack
Close to the angle of attack for max lift ot drag ratio. at large angle of attack. close to the critical angle of attack.

Question 78-7 : Aerofoils around a wing cross section aerodynamic lift is generated ?

At 75% due to reduced pressure on the upper wing surface.

exemple 102: At 75% due to reduced pressure on the upper wing surface
At 25% due to reduced pressure on the upper wing surface. at 25% due to increased pressure on the upper wing surface. at 75% due to increased pressure on the upper wing surface.

Question 78-8 : Aerofoils all other factors of importance remaining constant when angle of attack is increased ?

The drag increases.

exemple 106: The drag increases
The lift decreases. the lift increases but drag remains unaffected. the lift increases and drag decreases.

Question 78-9 : Stability the assistance control system stabilisation attitude altitude and guidance systems on a multi rotor aircraft is done by ?

On board electronic.

exemple 110: On board electronic
Servo-motors actuators electromagnets.

Question 78-10 : Stability the movement of an aircraft about the longitudinal axis is known as ?

Roll.

Question 78-11 : Stability for a fixed wing aircraft airplane or glider manoeuvrability around the lateral axis pitch ?

Depends on load distribution.

Question 78-12 : Stability for all fixed wing aircraft model you are able to change manoeuvrability onto lateral axis pitch by acting on ?

The center of gravity location.

exemple 122: The center of gravity location
The aerodynamic centre location. centre of pressure location. the load factor.

Question 78-13 : On a small fixed wing drone aircraft or glider the forward displacement of the centre of gravity will have the effect of ?

Increase the stall speed.

Question 78-14 : A fixed wing drone with a mass of 10 kg is performing a co ordinated level turn at a bank angle of 60° it will have an equivalent weight of ?

20 kg.

Question 78-15 : Choose the statement that best describes the stability concept of an aircraft ?

A stable aircraft tends to naturally resume its attitude after a disturbance.

Stability is the inherent quality of an aircraft to correct for conditions that may disturb its equilibrium and to return to or to continue on the original flightpath it is primarily an aircraft design characteristic the flightpaths and attitudes an aircraft flies are limited by the aerodynamic characteristics of the aircraft its propulsion system and its structural strength these limitations indicate the maximum performance and maneuverability of the aircraft if the aircraft is to provide maximum utility it must be safely controllable to the full extent of these limits without exceeding the pilot's strength or requiring exceptional flying ability if an aircraft is to fly straight and steady along any arbitrary flightpath the forces acting on it must be in static equilibrium the reaction of any body when its equilibrium is disturbed is referred to as stabilitypositive static stability the initial tendency of the aircraft to return to the original state of equilibrium after being disturbed
A stable aircraft is very manoeuvrable and requires dynamic compensation an aircraft is stable when the forces acting on it are equal. a stable aircraft is difficult to turn, climb or descent.



Exclusive rights reserved. Reproduction prohibited under penalty of prosecution.

1154 Free Training Exam