Analysis and Computer Program for Evaluation of Airbreathing Propulsion Exhaust Nozzle Performance
Final rept. Jun 1970-Nov 1972
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An analytical technique based on the time-dependent flow equations has been developed to predict the inviscid transonic flow field in axisymmetric propulsion nozzles. The analysis includes the treatment of axisymmetric nonuniform nozzle inlet profiles of total pressure, total temperature, specific heat, and molecular weight. The analysis is also capable of considering convergent-divergent, convergent, and shrouded or unshrouded plug nozzle geometries. A computer listing and three sample calculations are presented to illustrate some of the capabilities of the program.
- Fluid Mechanics
- Jet and Gas Turbine Engines