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)
a> v
b> v^2
c> v^3
d> v^(3/2)
1 answer
4 answers
1 answer
3 answers