As propulsion testing is undertaken at lower altitudes and higher Mach numbers, requirements of correct static temperature and pressure simulation and uniform flow in test section lead to stagnation temperatures too high to be produced by storage-type heaters; 10-Mw d-c plasma arc heater was developed at Johns Hopkins University for use with Mach 7 to 10 tunnel; thermal efficiencies exceeding 60% were achieved; design principles and operating characteristics of integrated arc heater and hypersonic propulsion tunnel.


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    Title :

    Application of d.c. plasma arc heating to hypersonic propulsion testing


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Raezer, S.D. (author) / Bunt, E.A. (author) / Olsen, H.L. (author)

    Published in:

    Publication date :

    1964


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Application of d.c. plasma arc heating to hypersonic propulsion testing

    BUNT, E. A. / OLSEN, H. L. / RAEZER, S. D. | AIAA | 1964


    Development of hypersonic propulsion tunnels using D.C. Plasma arc heating

    Raezer, S.D. / Bunt, E.A. / Olsen, H.L. | Engineering Index Backfile | 1963




    Hypersonic propulsion

    Anderson, G. Y. | NTRS | 1975