An aircraft is flying at a speed of 500 ft/s an altitude of 20,000 ft, where the atmospheric
temperature and pressure are 447.3°R and 972.5 lbf/ft2, respectively. If the inlet / diffuser
adiabatic efficiency is ?d = 0.92, compute the stagnation temperature and pressure at the
compressor face.
Rair = 1716 ft2/s2 –R cp,cold = 0.24 Btu/lbm-R cp,hot = 0.276 Btu/lbm-R cpAB = 0.29 Btu/lbm-R
?cold = 1.4 ?hot = 1.33 ?AB = 1.30