Flight on Mars and aerodynamics considerations
Based on basic equations of lift and drag forces, we can do rough estimation of the aerodynamics. The required power for leveled flight is given by the following equation, where &rho is air density, S wing area, v flight speed and C_{L} and C_{D} the lift and drag coefficients. If we assume that the airplane mass m is proportional to wing area S, we get:
This rough estimation shows us, considering that the solar power is proportional to the surface of the wing, that the feasibility of a solarpowered glider does in a first order estimation not depend on the size of the airplane or the flying speed. It is interesting to notice that for the same aerodynamics and the same surface, a flight on Mars will need (g'^{3}/&rho')^{1/2} = 2.1 times more power than on Earth. In order to reduce this power, efforts have to be concentrated on the aerodynamics (C_{L}, C_{D}) and the weight (m). One more problem is the very low Re number, which increases the difficulty of flight because the boundary layer is much less capable of handling an adverse pressure gradient without separation and the maximum lift capability is restricted.
