The NASA-Langley 14x22-ft subsonic wind tunnel has been used to ascertain the low speed aerodynamics of a conical-forebody/annular conformal propulsion system/truncated conical afterbody hypersonic-accelerator configuration with delta-planform wing. Six-component force-and-moment data were obtained over the -4 to +30 deg alpha range and + or - 20 deg sideslip. Flow visualization diagnostics were used to characterize configuration aerodynamics. Vortex flows from the conical forebody created large values of local inflow angles at the engine inlet locations on the lee side of the model, at the moderate-alpha values associated with takeoff and landing.
Wind-tunnel investigation of the low-speed aerodynamics of slender accelerator-type configurations
Aerospace Technology Conference and Exposition ; 1988 ; Anaheim, CA, United States
1988-01-01
Conference paper
No indication
English
Wind-Tunnel Investigation of the Low-Speed Aerodynamics of Slender Accelerator-Type Configurations
SAE Technical Papers | 1988
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