Ed Brown
ABSTRACT: When one wishes to predict or analyze rocket motor/engine performance accurately, a method for determining the nozzle thrust coefficient at each point in time is essential. If the vacuum thrust coefficient for the nozzle is known, the thrust coefficient for other conditions can easily be determined. This paper outlines several methods for determining the vacuum thrust coefficient in the hope that it will encourage this type of calculation and lead to new and better methods for simulation and analysis in the future.
Key Words: vacuum thrust coefficient, thrust coefficient, expansion ratio, specific heat ratio, chamber pressure, thrust, rocket propulsion theory
Ref: JPyro, Issue 6, 1997, pp9-16
(J6_9)
© Journal of Pyrotechnics and CarnDu Ltd
