Straight and Level Flashcards
In straight and level flight;
Thrust = Drag and Lift = Weight
True
If the CoG is behind the CoP, the lift/weight couple will tend to pitch the nose (up/down)?
Up
It is the function of the_____ to balance out the lift/weight and thrust/drag couples in flight.
Tail plane
If the weight of the aircraft is decreased in level flight the stalling speed will be (increased/decreased)
Decreased
With the an increase in altitude the power required curve moves up and to the _______
Right because TAS has increased
Range can be defined as:
Maximum distance an aircraft can travel with a given amount of fuel
Endurance is a measure of how long an aircraft can stay in the air on reserve fuel.
False
Why do we fly at the minimum power speed for best endurance?
Power is directly related to fuel burn. Therefore power ↓ = fuel ↓ = ↑ Endurance
During straight and level flight, if the power is reduced, the effect of the decrease in slipstream and power on a typical single engine aeroplane (DA40) will be:
Nose pitch down, yaw to the right, decrease in elevator/rudder effectiveness
In a piston engined aeroplane, maximum range is achieved by flying at the indicated airspeed which:
Creates the minimum total drag
For a typical A/C thrust acts (below/above) drag, therefore creating a nose (down/up) moment.
Below / up
To fly at a slower airspeed
To fly at a faster airspeed
Power ↓ Attitude ↑,
Power ↑ Attitude ↓
Why does Power available reduce, and not remain constant?
Losses due to propeller inefficiency
An aircraft in straight and level flight is considered to be in equilibrium.
True’.
The CoP (centre of pressure) can be defined as:
Point at which the lift forces acting on a body can be summarised to act through
In a piston-engined aircraft, the least amount of power is required for steady straight and level flight:
At a lower speed than the minimum drag speed
When lowering landing gear, the total drag line moves (upwards/downwards). This will create a (nose down/nose up) moment?
Downwards / down
The drag at any aircraft weight and IAS remains constant regardless of altitude.
True’
What is correct with regards to flying for Range when applying the following formula:
“Energy = Force x distance”
Where energy = fuel, force = thrust and distance = distance traveled
Energy (fuel) = Force ↓ x Distance ↑
The best range speed (still air) is the speed for minimum drag. If altitude is increased, the best range speed is affected how?
IAS remains constant, TAS increases
Endurance is defined as;
Time spent in the air with a given amount of fuel, regardless of distance
Consider this C172, who has the International endurance record, flying for 65 days - nonstop. How would they best configure the aircraft?
Min power speed
Low rpm, mixture leaned
Lowest safe altitude
Low weight
What changes in aeroplane control must be made to maintain straight and level flight whilst the airspeed is being increased from normal cruising speed?
Decrease the angle of attack to compensate for the increase in airspeed
Why does Power available reduce, and not remain constant?
Losses due to propeller inefficiency
What would the requirements be for an aircraft to fly for best range,
Low weight Min drag speed Flaps and gear up Full throttle height Tail wind Mixture leaned
What happens to TAS (true airspeed) with an increase in altitude, when maintaining a constant IAS (indicated airspeed)?
Increases because density reduces, therefore to maintain the same IAS the aircraft must travel faster, therefore increasing TAS.
With an increase in weight, the power required curve will move (Up/Down)
Up
