A static thrust stand is designed for testing a jet engine. The following conditions are expected for a typical test: intake air velocity = 200 m/s, exhaust gas velocity = 500 m/s, intake and exit cross-sectional areas = 1 m, intake static pressure = -22.5 kPa (= 78.5 kPa absolute), exhaust static pressure = 0 kPa (101 kPa absolute), density of air p=1.021 kg/m³. Estimate the thrust reaction force to design the test stand to carry, if it must have a safety factor of 3.
Control surface
Turbojet engine
Force on the flow
dS
V1
A1
P1
dS
V2
A2
P2
Reaction force on stand