An aerodynamic computer code was developed for calculating the pressure distribution on a missile or its components, e.g., body and wings and subsequently interpolating the results by surface fit at locations as specified for structural analysis using the NASTRAN computer code. The code is valid for high supersonic speeds and generalized attitudes of the missile. (Author)
Aerodynamic Computer Code for Computing Pressure Loads on a Missile at High Supersonic Speeds and Generalized Attitudes
1979
232 pages
Report
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Englisch