Accession Number : AD0831249

Title :   WING-BODY INTERACTIONS AT A MACH NUMBER OF 9.5.

Descriptive Note : Research and development rept.,

Corporate Author : DAVID W TAYLOR NAVAL SHIP RESEARCH AND DEVELOPMENT CENTER BETHESDA MD AVIATIO N AND SURFACE EFFECTS DEPT

Personal Author(s) : Ellis, Bertram K. ; Furey, Roger J.

Report Date : SEP 1967

Pagination or Media Count : 43

Abstract : Several delta wing-body configurations were tested at a Mach number of 9.5 to determine the effects of the radius of curvature of the wing-body junction on the spanwise pressure and aerodynamic heating distributions. The results indicate that although the pressure levels longitudinally may change there is essentially no pressure variation along the span resulting from the change in said radius of curvature; however, there is considerably spanwise variation in the values of aerodynamic heating. These variations in general, agree with the theoretical predictions of hypersonic flow in a corner alined with the free-stream velocity. Finally, heating distribution and oil flow visualization pictures confirm the theoretically predicted vortical flow in the region of the wing-body juncture. (Author)

Descriptors :   (*WING BODY CONFIGURATIONS, HYPERSONIC CHARACTERISTICS), DELTA WINGS, AERODYNAMIC HEATING, FLOW VISUALIZATION, ANGLE OF ATTACK, WIND TUNNEL MODELS, INTERACTIONS, MACH NUMBER, CURVE FITTING, SCHLIEREN PHOTOGRAPHY, PRESSURE, CURVED PROFILES, REYNOLDS NUMBER.

Subject Categories : Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE