3.3. Using the BEMT, show the effect of increasing linear twist on the variations in inflow, thrust, induced power, profile power, and lift coefficient across the span of a rotor with four blades of rectangular planform and solidity 0.1, and operating at a thrust coefficient of 0.008. Assume Cdo = 0.01. Include Prandtl tip-loss effects. All of the results should be compared at a constant thrust (disk loading). 3.4. For the same rotor parameters as used in the previous question, compute the power required to hover versus thrust for different values of linear blade twist. Also compute the figure of merit and induced power factor versus thrust coefficient. Assume that the profile drag is given by C = 0.01 + 0.025a + 0.65a. Show your results graphically. Include the Prandtl tip-loss function. Comment on your results. Problem = Leishman (2nd Ed.) problem 3.3, but without consideration of tip loss effects. Also, use the following (instead of the values given in the problem): CT = 0.009, = 0.105, and Cdo 0.012. Consider the following linear twist values: Otw = 0, -5, -10, -15,-20,-25 deg. Leishman (2nd Ed.) problem 3.4, but tailored to problem 1 herein. No need to consider tip loss effects.