The aerodynamic drag on an aeroplane is given by D=bv^2. The power output of the aeroplane cruising at constant speed in level flight is proportional to
a> v
b> v^2
c> v^3
d> v^(3/2)
To determine the power output of the airplane cruising at constant speed in level flight, we need to consider the relationship between power and the variables given in the equation for aerodynamic drag.
The formula for power is given by P = F × v, where P is power, F is force, and v is velocity. In this case, the force (F) will be the aerodynamic drag (D).
Given that the aerodynamic drag is given by D = bv^2, we can substitute this into the formula for power:
P = D × v
P = (bv^2) × v
P = bv^3
From this, we can see that the power output of the airplane is proportional to v^3.
Therefore, the correct answer is c> v^3.