On the Calculation of Thrust Coefficient.
PROPELLANTS EXPLOSIVES AND ROCKET MOTOR ESTABLISHMENT WESTCOTT (ENGLAND)
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The thrust of a rocket motor is generally calculated from the stagnation pressure, the throat area, and a non-dimensional thrust coefficient dependent upon the nozzle expansion area ratio. A comparison is made between momentum balance and pressure integral methods of calculating the ideal vacuum thrust coefficient, and the results used to examine how corrections should be made for nozzle divergence, skin friction and two-phase flow to obtain the real thrust coefficient of the motor. Author
- Numerical Mathematics
- Fluid Mechanics
- Rocket Engines