Final answer:
In straight and level unaccelerated trimmed flight, the lift of the wing and the tail can be calculated based on the weight distribution of the aircraft. The drag of the wing and the tail can be determined using the drag equation. The thrust of the engine is the force required to overcome drag and maintain the aircraft's speed. The lift-to-drag ratio is a measure of the efficiency of an aircraft.
Step-by-step explanation:
In straight and level unaccelerated trimmed flight, the lift of the wing and the lift of the tail of an aircraft depend on the weight distribution of the aircraft. The wing lift is responsible for supporting most of the aircraft's weight while the tail lift provides stability and control. The lift of the wing can be calculated using the formula:
Lift of the wing = (Weight of the aircraft × g) / Number of wings
The drag of the wing and the drag of the tail are the aerodynamic forces that oppose the forward motion of the aircraft. These forces can be calculated using the drag equation:
Drag force = 0.5 × Air density × Velocity squared × Wing area × Drag coefficient
The thrust of the engine is the force produced by the engines to overcome drag and maintain the aircraft's speed. The thrust required can be calculated using the thrust equation:
Thrust required = Drag force + Weight of the aircraft × g
The lift-to-drag ratio is a measure of the efficiency of an aircraft. It is calculated by dividing the lift force by the drag force:
Lift-to-drag ratio = Lift force / Drag force