Accession Number : AD0282651

Title :   HYPERSONIC VISCOUS FLOW OVER CONES AT NOMINAL MACH 11 IN AIR

Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : ANDERSON,JOHN D. JR.

Report Date : JUL 1962

Pagination or Media Count : 1

Abstract : Experimental results were obtained on weakinteraction, self-induced pressures on cones at nominal Mach 11 in air using the ARL 3-inch continuous flow hypersonic wind tunnel. The results at zero angle of attack were compared with Probstein's first-order weak-interaction theory (AD66 227) and with Talbot's numerical method for predicting self-induced pressures (AD-204 704). Theory agreed well with the experimental data for 5-degree and 10-degree semivertex angle cones, but overestimated the experimental induced pressures for 15-degree and 20-degree cones. The results were correlated reasonably well by the hypersonic viscous-interaction parameter and the hypersonic similarity parameter. The experimental results obtained for the 10-, 15-, and 20-degree cones at angles of attack from -15 to 15 degrees compared favorably with Newtonian theory for angles of attack greater than 3 degrees. For values less than 3 degrees, Newtonian theory did not agree with the experimental results. (Author)

Descriptors :   *CONICAL BODIES, AERODYNAMIC CHARACTERISTICS, FLUID FLOW, HYPERSONIC CHARACTERISTICS, HYPERSONIC FLOW, LAMINAR BOUNDARY LAYER, MODEL TESTS, PRESSURE, THEORY, WIND TUNNEL MODELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE