how to calculate the air flow rate of a "university olympus" jet engine. With the given details: RPM$=37000,$ P$1=-1226\mathrm{.}92,$ P$3=19328\mathrm{.}77,$ PT$3=19116\mathrm{.}2,$ PT$4=18477\mathrm{.}27,$ PT$5=2688,3,$ TT$3=306\mathrm{.}81,$ TT$4=810\mathrm{.}76,$ TT$5=710\mathrm{.}23,$ TT$6=690\mathrm{.}04,$ EGT$=506,$ Fuel flow rate$=0\mathrm{.}257364,$ Thrust$=11\mathrm{.}657$