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 (F.) intake air velocity = 214 m/s exhaust gas velocity = 500 m/s intake cross section area = 0.93 m intake static pressure = -22.7 kPa, 78.6 kPa (abs) intake static temperature = 267 K exhaust gas pressure = 0 kPa R=287 kJ/kg.K a P 1 pdf + pV d4 = 0 ; | V,V -ndA = IF; P= L Vp dF + RT r at es Write the x-component of the equation and simplify (just one line!) Obtain the algebraic form of the x- component (just one or two lines at most!) Recast the equation obtained in the previous step to give the Fx (just one line!) [ Show that mass flow rates are equal at inlet and exit (using mass conservation eq.) (just one or two lines at most!) Calculate the density at inlet (just one or two lines at most!) Put the other values and calculate the [control volume Thrust Force Fx (just one or two lines at most!) 1. a