Accession Number : AD0673895

Title :   RESEARCH ON HYPERSONIC FLOW OF BLUNT DELTA WINGS. PART I. THEORETICAL AND EXPERIMENTAL STUDY OF A 70-DEGREE BLUNT DELTA WING FOR LOW ANGLES OF ATTACK AT SUPERSONIC AND HYPERSONIC SPEEDS.

Descriptive Note : Final rept. Nov 66-Nov 67,

Corporate Author : ARA INC WEST COVINA CALIF

Personal Author(s) : Mazelsky,Bernard ; Chao,Chia-Chun ; Liu,Mei-Kao

Report Date : NOV 1967

Pagination or Media Count : 82

Abstract : The object of the present analysis is to investigate the high-speed aerodynamic properties of a blunt delta wing at low angles of attack where the maximum lift to drag ratio occurs. Oguchi's solution of hypersonic flow over a blunt leading edge flat plate at zero incidence is extended to three dimensional delta wings at angle of attack. The shock wave shapes and pressure distributions were obtained by employing the oblique shock relations at the windward sides of the Prandtl-Meyer equations at the leeward side of the wing. The total lift and drag of the wing due to pressure and skin friction were computed by numerical integration using the IBM 7094 computer. The present calculated aerodynamic forces generally agree with the experimental data at the high supersonic Mach numbers (M approx. > or = 4) and lower thickness ratio of the wing which is a 70-degree swept slab sided delta wing with a cylindrical leading edge. (Author)

Descriptors :   (*DELTA WINGS, HYPERSONIC CHARACTERISTICS), BLUNT BODIES, ANGLE OF ATTACK, SUPERSONIC CHARACTERISTICS, THREE DIMENSIONAL FLOW, SHOCK WAVES, LIFT, DRAG, SKIN FRICTION, NUMERICAL INTEGRATION, THICKNESS, LEADING EDGES, CYLINDRICAL BODIES, PRESSURE, DISTRIBUTION

Subject Categories : Aerodynamics
      Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE