An aircraft model tested in a wind tunnel produced 5 pounds of lift, giving a lift coefficient of 0.7. When the actual aircraft with a wing area of 650 ft^2 is in steady, level flight at altitude and the same angle of attack as the wind tunnel tests, the flight parameters are rho = 0.002 slug/ft3 and V_infinity = 400 ft/s.
a. How much does the actual aircraft weigh? Assume that the wind tunnel test conditions can be appropriately scaled to flight conditions (matched Mach number and Reynolds number, to be discussed later in the course).
b. Describe the value of using dimensionless coefficients in this case.