A wind tunnel test of a one-thirtieth scale 'B' series Atlas missile with operating rocket engines was run at the NACA Lewis 8-by-6 foot supersonic wind tunnel. The primary test objective was to determine the amount of rocket and gas turbine exhaust recirculation into the missile base region; a secondary objective was to determine the effect of operating rockets on missile skin and base pressure. Only the pressure data are considered in this report. (Author)


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    Title :

    A Preliminary Analysis of Rocket Exhaust Jet Effects on Missile Skin and Base Pressures at Mach 0.6 and 1.5 - Naca Lewis Flight Propulsion Laboratory Test 2093


    Contributors:

    Publication date :

    1958


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English