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A wind tunnel test was conducted to obtain the surface pressure distributions of three elliptic missile body configurations. The test was performed at nominal Mach numbers from 0.4 to 1.3 at a constant nominal free-stream unit Reynolds number of 2.4 million per ft. The angle-of-attack range was -4 to 20 deg at sideslip angles of -4, 0, and 4 deg. Only sample tabulations of the test results are included in the report. Keywords: Elliptic bodies, Power law bodies, Pressure test, Transonic flow.
A wind tunnel test was conducted to obtain data on the aerodynamic characteristics of three elliptic missile body configurations. The test was performed at nominal Mach numbers from 0.4 to 1.3 at a constant nominal free-stream unit Reynolds number of 2.4 million per ft. The angle-of-attack range was -4 to 20 deg at sideslip angles of 0 and 4 deg. Only sample tabulations of the test results are included in the report.
This two-volume set includes discussions of the physics of the fluid mechanics phenomena associated with tactical missile flight and the full range of prediction methods required to analyze current and future missiles. It's a valuable resource for missile aerodynamicists, designers, and researchers.