Experimental Studies on Aerodynamic Characteristics of SSTO Vehicle at Low Subsonic Speeds 911981
As for a fully reusable space transportation system of a single stage to orbit(SSTO) of horizontal take-off and landing type, experimental studies on low-speed aerodynamic characteristics have been done. The wind tunnel tests were conducted using NAL's gust wind tunnel. Six-component force and moment data were obtained over an angle of attack range from -14° to 44°. In this paper, the aerodynamic test results are presented for the low-speed aerodynamics of a generic SSTO configuration.
Citation: Miyamoto, Y., Fujita, T., Iwasaki, A., and Fujieda, H., "Experimental Studies on Aerodynamic Characteristics of SSTO Vehicle at Low Subsonic Speeds," SAE Technical Paper 911981, 1991, https://doi.org/10.4271/911981. Download Citation
Event:
International Pacific Air & Space Technolgy Conference
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
International Pacific Air and Space Technology Conference and 29th Aircraft Symposium Proceedings-P-246, SAE 1991 Transactions - Aerospace-V100-1
Related Topics:
Wind tunnel tests
Aerodynamics
Entry, descent, and landing
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