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

\[ \begin{aligned} \text { intake air velocity } & =700 \mathrm{ft} / \mathrm{s} \\ \text { exhaust gas velocity } & =1640 \mathrm{ft} / \mathrm{s} \\ \text { intake cross section area } & =10 \mathrm{ft}^{2} \\ \text { intake static pressure } & =11.4 \mathrm{psia} \\ \text { intake static temperature } & =480^{\circ} \mathrm{R} \\ \text { exhaust gas pressure } & =0 \mathrm{psi} \end{aligned} \]

Estimate a nominal thrust to design for.