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Computer-aided space shuttle orbiter wing design studyAn 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.
Document ID
19740014398
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Phillips, W. P. (NASA Langley Research Center Hampton, VA, United States)
Decker, J. P. (NASA Langley Research Center Hampton, VA, United States)
Rau, T. R. (NASA Langley Research Center Hampton, VA, United States)
Glatt, C. R. (Aerophysics Res. Corp. Hampton, Va., United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Publication Information
Publisher: NASA
Subject Category
Space Vehicles
Report/Patent Number
NASA-TN-D-7478
L-9099
Report Number: NASA-TN-D-7478
Report Number: L-9099
Accession Number
74N22511
Funding Number(s)
PROJECT: RTOP 502-37-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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