Calculating the thrust of the engine:
When applying the above method to calculate the individual thrust loads on the various components it is assumed that the engine is static. The effect of aircraft forward speed on the engine thrust will be dealt with later. In the following calculations ‘g' is taken to be 32 for convenience.
To obtain the thrust on the compressor casing, it is necessary to calculate the conditions at the inlet to the compressor and the conditions at the outlet from the compressor. Since the pressure and the velocity at the inlet to the compressor are zero, it is only necessary to consider the force at the outlet from the compressor. Therefore, given that the compressor - OUTLET Area (A) = 182 sq. in. Pressure (P) = 94 lb. per sq. in. (gauge) Velocity (vj) = 406 ft. per sec. Mass flow (W) = 153 lb. per sec.
The thrust = (A*P) + WVj/g-0 = (182*94) + (153*406)/32-0 = 19,049lb. of thrust in a forward direction.