Downwash angle measurements were made near tail location behind high- aspect-ratio wing at Mach numbers up to 0.89. Variations of downwash angle with normal-force coefficient are approximately equal at Mach number up to highest test value for normal-force coefficient up to stall condition. Downwash angle for given normal-force coefficient varies only slightly at Mach numbers up to approximately 0.83, but decreases approximately 0.4 Degrees when Mach number is increased to highest test value.
Investigation of the Downwash at the Probable Tail Location Behind a High-Aspect-Ratio Wing in the Langley 8-Foot-High-Speed Tunnel
1947
16 pages
Report
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English