An analytical and experimental investigation has been made to provide a space shuttle orbiter wing design that met the guideline requirements of landing performance, stability, and hypersonic trim for a specified center-of-gravity envelope. The analytical study was facilitated by the use of the Optimal Design Integration system (ODIN) and the experimental part of the investigation was conducted in the Langley low-turbulence pressure tunnel and the Langley continuous-flow hypersonic tunnel.
Computer-aided space shuttle orbiter wing design study
1974-05-01
Miscellaneous
No indication
English
Computer-aided space shuttle orbiter wing design study
TIBKAT | 1974
|Computer-Aided Space Shuttle Orbiter Wing Design Study
NTIS | 1974
|Wing optimization for space shuttle orbiter vehicles
NTRS | 1972
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