The characteristics of the Langley 34 cm (13.5 in.) pilot cryogenic transonic pressure tunnel are described, and the results of initial tunnel operation are presented. Tests of a two-dimensional airfoil at a Mach number of 0.85 show identical pressure distributions for a chord Reynolds number of 8,600,000 obtained first at a stagnation pressure of 4.91 atmospheres at a stagnation temperature of +120 F and then at a stagnation pressure of 1.19 atmospheres at a stagnation temperature of -250 F.


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    Title :

    Flight simulation characteristics of the Langley high Reynolds number cryogenic transonic tunnel


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

    Conference:

    Aerospace Sciences Meeting ; 1974 ; Washington, DC


    Publication date :

    1974-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Flight Simulation Characteristics of the Langley High Reynolds Number Cryogenic Transonic Tunnel

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




    Test results from the Langley high Reynolds number cryogenic transonic tunnel

    RAY, E. / KILGORE, R. / ADCOCK, J. et al. | AIAA | 1974


    Test results from the Langley high Reynolds number cryogenic transonic tunnel

    Ray, E. J. / Kilgore, R. A. / Adcock, J. B. et al. | NTRS | 1974