Accession Number : AD0725606

Title :   The Investigation for the Aerodynamic and Heat Transfer Characteristics of Slender Hypersonic Cones over a Wide Range of Angles of Attack.

Descriptive Note : Technical rept. no. 4, 1 Jan 69-30 May 71,

Corporate Author : CATHOLIC UNIV OF AMERICA WASHINGTON D C DEPT OF MECHANICAL ENGINEERING

Personal Author(s) : Chang,Paul K. ; Oh,Sin K. ; Smith,Russell A. ; Yim,B. H. ; Jettmar,R. U.

Report Date : 30 MAY 1971

Pagination or Media Count : 133

Abstract : The problems of aerodynamic and heat transfer characteristics of slender sharp nosed hypersonic cones over a wide range of angles of attack are examined and the analytical solutions are presented. Three particular problems are studied: (1) inviscid flow characteristics of shock layer involving laminar separation in the leeward side with undisturbed free stream Mach number 7.95 and angle of attack 20 degrees for cone half angle 10 degrees, (2) attached three-dimensional compressible boundary layer over the cone, (3) aerodynamic and heat transfer characteristics of turbulent separated flow. (Author)

Descriptors :   (*REENTRY VEHICLES, *AERODYNAMIC HEATING), HEAT TRANSFER, CONICAL BODIES, BOUNDARY LAYER TRANSITION, ANGLE OF ATTACK, SHOCK WAVES, HYPERSONIC CHARACTERISTICS, SLENDER BODIES, NUMERICAL METHODS AND PROCEDURES, MATHEMATICAL MODELS, FLOW SEPARATION, COMPUTER PROGRAMMING

Subject Categories : Guided Missile Reentry Vehicles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE