Publikationsdatum:
2019-06-27
Beschreibung:
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.
Schlagwort(e):
SPACE VEHICLES
Materialart:
NASA-TN-D-7478
,
L-9099
Format:
application/pdf
