Abstract

References 1 lannuzi, F. A. and Weddington, E. D., Free Pressure across the of Sharp and Blunt 10-degree Cones at Mach Numbers from 15 to 20, TR 66-223, Dec. 1966, Arnold Engineering Development Center, Tullahoma, Tenn. 2 Softley, E. J. and Graber, B. C, An Study of the Pressure and Heat Transfer on the of Cones in Hypersonic Flow, AGARD, CP 19, May 1967. 3 Murman, E. M., Experimental Studies of a Hypersonic Cone Wake, AIAA Journal, Vol. 7, No. 9, Sept. 1969, pp. 1724-1730. 4 Cassanto, J. M. and Hoyt, T. L., Flight Showing the Effect of Mass Addition on Pressure, AIAA Journal, Vol. 8, No. 9, Sept. 1970, pp. 1705-1707. 5 Cassanto, J. M., Flight Test Pressure at Hypersonic Mach Numbers in Turbulent Flow, AIAA Journal, Vol. 10, No. 3, March 1972, pp. 329-331. 6 Cassanto, J. M., Radial Pressure Gradients in Flow, AIAA Journal, Vol. 5, No. 12, Dec. 1967, pp. 2278-2279. 7 Cassanto, J. M., Ratio on Pressure, AIAA Journal, Vol. 3, No. 12, Dec. 1965, pp. 2351-2352. 8 Sherman, M. M. and Nakumura, T., Flight Test Measurements of Boundary Layer Transition on a Non-Ablating 22° Cone, Journal of Scientific Research, Vol. 7, No. 2, Feb. 1970, pp. 137-142. 9 U.S. Standard Atmospheric Supplements, 1966, 15° N. Annual. 10 Ohrenberger, J. T. and Baum, E., Laminar Near Wake Solutions under Atmospheric Entry Conditions, AIAA Paper 72-116, San Diego, Calif., 1972. 11 Ohrenberger, J. T. and Baum, E., A Theoretical Model of the Near Wake of a Slender Body in Supersonic Flow, AIAA Journal, Vol. 10, No. 9, Sept. 1972, pp. 1165-1172. 12 Van Hise, V., of Variation in Pressure over the Reynolds Number Range in which Wake Transition Occurs for Two-Dimensional Bodies at Mach Numbers from 1.95 to 2.92, TN D-167, Nov. 1959, NASA. 13 Kavanau, L. L., Results of Some Based Pressure Experiments at Intermediate Reynolds Numbers with M = 2.84, Journal of Aerospace Sciences, Vol. 21, April 1954; also Base Pressure Studies in Rarefied Supersonic Flows, Preprint 529, Jan. 1955, Institute of Aerospace Sciences, 14 Batt, R. G. and Kubota, T., Experimental Investigation of Near Wakes behind 20° Wedges at M^ = AIAA Journal, Vol. 6, No. 11, Nov. 1968, pp. 2077-2083. 15 Chapman, D. R., An Analysis of Pressure at Supersonic Velocities and Comparison with Experiment, Rept. 1051, May 1950, NACA.

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