[10 points] you are performing experiments on a model of a new commercial airliner in a pressurized wind tunnel. the full scale vehicle you are trying to model flies at 33,000 ft with a freestream mach number . the wingspan of the airplane is 150 ft and the planform area is 1230 ft2 , which gives a mean chord length of 8.2 ft. the largest model you can fit in the tunnel has a wingspan of 6 feet. the wind tunnel can be pressurized, but it runs with the test section at standard atmospheric temperature at sea level. since the speed of sound and viscosity are dependent on temperature but not on pressure, the speed of sound and the viscosity in the wind tunnel have the same values they do in the standard atmosphere at sea level. (a) determine what pressure is needed in the wind tunnel in order to achieve dynamic similarity. (assume air is an ideal gas.) (b) if the drag measured on the model is d = 225 lbf , what is the dimensional drag on the fullscale airplane going to be? (c) if the pitching moment measured on the model is m = 250 ft-lbf , what is the dimensional moment on the full-scale airplane going to be? (note: you do not need to know what a pitching moment is, just treat it as some moment measured about some axis.)