Accession Number : AD0646665

Title :   HYPERSONIC FLOW OF BLUNT DELTA WINGS AT LOW ANGLES OF ATTACK. I. SHOCK WAVE SHAPE AND SURFACE PRESSURE DISTRIBUTION.

Descriptive Note : Final rept.,

Corporate Author : ARA INC WEST COVINA CALIF

Personal Author(s) : Mazelsky,Bernard ; Liu,M.

Report Date : NOV 1966

Pagination or Media Count : 62

Abstract : This report covers a portion of a research program on the aerodynamic characteristics of a cylindrical-leading-edge 70 degrees swept delta wing at high supersonic and moderate hypersonic Mach numbers, and for small values of angle of attack. Prior to the calculation of the lift and drag characteristics of the wing, a semi-empirical method was developed to predict the shock wave shape surrounding the wing as well as the corresponding pressure distribution on the wing surface. The theoretical shock shape and pressure distribution results are compared with experiments available from the open literature as well as with experimental pressure distributions obtained in the present program on the tip portion of a blunt 70 degrees swept delta wing. Within the range of applicability of the semi-empirical method, the predicted shock wave shapes are in good agreement with experiment. The calculated pressure distributions agree quite well with experiment, provided the angle of attack is below 15 degrees and the Mach number is above M = 3.0.

Descriptors :   (*DELTA WINGS, AERODYNAMIC CHARACTERISTICS), (*AERODYNAMIC CHARACTERISTICS, SWEPT WINGS), SUPERSONIC FLOW, HYPERSONIC FLOW, MACH NUMBER, ANGLE OF ATTACK, SHOCK WAVES, WIND TUNNELS, LIFT, DRAG, BLUNT BODIES, AERODYNAMIC CONFIGURATIONS

Subject Categories : Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE