A rotor has a rectangular blade planform, a solidity of 0.1, ideal blade twist, and operates in hover at a thrust coefficient of 0.008. By numerical means, using the combined blade element momentum theory (BEMT), compare the predicted inflow ratio across the span of the blade with the exact (analytic) result (uniform inflow result). Plot continuous line for exact result and points (markers) for numerical result. Show also the radial distributions of thrust, induced torque, lift coefficient, and the compare the solutions obtained using the exact theory. Compare the numerical calculations of the integrated thrust and induced power with exact results for this rotor over the range 0 < CT < 0.01.