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A static thrust stand is to be designed for testing a specific jet engine. Knowing the following conditions for a typical test, estimate a nominal thrust to design for.

$)=(287\frac{J}{k}g*K$

intake air velocity exhaust gas velocity intake cross section area intake static pressure intake static temperature exhaust gas pressure

$=214\frac{m}{s}$

$=500\frac{m}{s}$

$=0\mathrm{.}93m^2$

$=-22\mathrm{.}7$kPa,$78\mathrm{.}6$kPa $abs$

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