A static thrust stand is to be designed for testing a specific jet engine. Knowing the following conditions for a typical test,
intake air velocity = 700 ft/s
exhaust gas velocity = 1640 ft/s
intake cross section = 10 ft^2
intake static pressure = 11.4 psia
intake static tempature = 480 degree R
exhaust gas pressure = 0 psi
estimate a nominal thrust to design for.