A pilot transonic cryogenic pressure tunnel has recently been developed and proof tested at the NASA Langley Research Center. In addition to providing an attractive method for obtaining high Reynolds number results at moderate aerodynamic loadings and tunnel power, this unique tunnel allows the independent determination of the effects of Reynolds number, Mach number, and dynamic pressure (aeroelasticity) on the aerodynamic characteristics of the model under test. The proof of concept experimental and theoretical studies are briefly reviewed. Experimental results obtained on both two- and three-dimensional models have substantiated that cryogenic test conditions can be set accurately and that cryogenic gaseous nitrogen is a valid test medium. (Author)


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    Title :

    Analysis of Validation Tests of the Langley Pilot Transonic Cryogenic Tunnel


    Contributors:
    E. J. Ray (author) / R. A. Kilgore (author) / J. B. Adcock (author) / E. E. Davenport (author)

    Publication date :

    1975


    Size :

    22 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Analysis of validation tests of the Langley pilot transonic cryogenic tunnel

    Ray, E. J. / Kilgore, R. A. / Adcock, J. B. et al. | NTRS | 1975


    Analysis of Validation Tests of the Langley Pilot Transonic Cryogenic Tunnel

    Edward J. Ray / Robert A. Kilgore / Jerry B. Adcock et al. | AIAA | 1975




    Simulation of flight test conditions in the Langley pilot transonic cryogenic tunnel

    Kilgore, Robert A. / Adcock, Jerry B. / Ray, Edward J. | TIBKAT | 1974