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- W2003305384 abstract "NASA has recently developed and proof tested a pilot cryogenic transonic pressure tunnel. In addition to providing an attractive method for obtaining high Reynolds number results at moderate aerodynamic loadings and tunnel power, this unique facility enables the independent determination of the effects of Reynolds number, Mach number, and aeroelasticity. The proof-of-concept experimental and theoretical studies are briefly reviewed. Experimental results are included which indicate pressure distributions for a two-dimensional airfoil and strain-gage balance characteristics for a three-dimensional delta wing model." @default.
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- W2003305384 date "1974-07-08" @default.
- W2003305384 modified "2023-09-27" @default.
- W2003305384 title "Test results from the Langley high Reynolds number cryogenic transonic tunnel" @default.
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- W2003305384 doi "https://doi.org/10.2514/6.1974-631" @default.
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