Aerothermal environment in control surface gaps in hypersonic flow - An overviewExperimental and analytical research by the NASA Langley Research Center to develop an understanding of the fluid and thermal environment in control surface gaps such as the spanwise gap of the wing elevon and chordwise gap of a split elevon configuration typical of the Space Shuttle are summarized. Although the experimental and analytical studies were initiated too late to significantly impact the basic Shuttle design they do provide a fundamental understanding of the basic fluid/thermal environment in control surface gaps and help to establish a firm data base for future vehicle design.
Document ID
19830051514
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wieting, A. R. (NASA Langley Research Center Hampton, VA, United States)
Walsh, J. L. (NASA Langley Research Center Hampton, VA, United States)
Bey, K. S. (NASA Langley Research Center Loads and Aeroelasticity Div., Hampton, VA, United States)