Design of supersonic aircraft and missiles requires information about heat transfer coefficients and temperature recovery factors for supersonic speeds that extend over wide range of Reynolds number; extension of investigation reported in Tech Note 3303, indexed in Engineering Index 1954 p 9, to measurement of Mach number of 2.06.


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    Title :

    Turbulent-heat-transfer measurements at Mach number of 2.06


    Additional title:

    NACA -- Tech Note


    Contributors:
    Brevoort, M.J. (author) / Rashis, B. (author)


    Publication date :

    1955


    Size :

    20 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    Turbulent-heat-transfer measurements at a Mach number of 2.06

    Brevoort, Maurice J / Rashis, Bernard | NTRS | 1955


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    Brevoort, Maurice J. / Rashis, Bernard | TIBKAT | 1955


    Wind tunnel measurements of wrap around fins at Mach 2.06

    Abbate, Gregg / Berner, Claude | AIAA | 1994


    Wind Tunnel Measurements of Wrap Around Fins at Mach 2.06

    Abate, G. / Berner, C. / AIAA | British Library Conference Proceedings | 1994


    Turbulent-heat-transfer measurements at Mach number of 3.03

    Brevoort, M.J. / Rashis, B. | Engineering Index Backfile | 1954