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Why? Because: “Lift is proportional to the density of the air and approximately proportional
to the square of the flow speed.”
Lift also depends on the size of the wing, being generally proportional to the wing's area projected in the lift direction. In calculations it is convenient to quantify lift in terms of a lift coefficient based on these factors.
The lift force depends on the shape of the airfoil, especially the amount of camber (curvature such that the upper surface is more convex than the lower surface, as illustrated at right). Increasing the camber generally increases lift.
The low density of the Martian atmosphere and the relatively small Mars Helicopter rotor result in very low chord-based Reynolds number flows, 𝑅𝑒#=𝑂(103−104). At low Reynolds numbers,flat and cambered plates can outperform conventional airfoils,making them of interest for the Mars Helicopter rotor.
When the littler airplane got up to altitude, the margin between the climb speed and the critical Mach number and stall became very, very minor, and we were looking at plus or minus two-and-a-half knots at one particular point in the climb between the climb schedule and critical Mach and stall speed so that’s very very small. When we got the bigger airplanes, we got up to plus or minus seven-and-a-half knots of margin.