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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,
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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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
APPROVED FOR PUBLIC RELEASE