An aircraft is flying at mach 0.65 at 14,000 ft. what are the standard conditions at this altitude? what is the true airspeed of the aircraft? what would the total pressure measured by a pitot probe be? what would be the temperature at the head of the pitot probe? at some point on the aircraft, the velocity is increased by 10%. what would the temperature be at this point? you will need the specific heat: c_p=6006 □((ft*lb)/(slug*°r))=1008□(j/(kg*k) ) what is the new pressure at the point in part "e"? what is the new density at the point in part "e"?