Theoretical flow-fields have been calculated for various nozzle/launch-tube configurations using this flow model. The solutions, thus calculated, are compared with experimental data in the present paper. The principal objectives of the present paper are (1) to present an engineering model for the impingement flow-field which is produced when an underexpanded supersonic nozzle is exhausted into a constant-area tube, (2) to compare the computed flow-field solutions with experimental results, and (3) to use the comparisons to establish the validity of the flow model. (Author)
The Analysis of Secondary Flows for Tube-Launched Rocket Configurations
1981
50 pages
Report
No indication
English
Rockets , Aerodynamics , Flow fields , Aerodynamic configurations , Rocket launchers , Secondary flow , Mathematical models , Launch tubes , Tube launched , Free flight models , Nozzle gas flow , Gas flow , Fluid flow , Mass flow , Exhaust nozzles , Supersonic nozzles , Plumes , Shock waves , Impingement , Jet mixing flow , Mathematical analysis , Blow by flow
Secondary flows for a tube-launched rocket configuration
AIAA | 1980
|Secondary Flows in a Rocket Launcher Tube
AIAA | 1981
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