Accession Number : AD0698779

Title :   TABLES OF INVISCID SUPERSONIC FLOW ABOUT CIRCULAR CONES AT INCIDENCE GAMMA = 1.4. PART I,

Corporate Author : ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT PARIS (FRANCE)

Personal Author(s) : Jones,D. J.

Report Date : NOV 1969

Pagination or Media Count : 531

Abstract : The report provides tabulated results for the inviscid flow field about several circular cones at incidence to a uniform supersonic stream (gamma = 1.4). The three velocity components, pressure and density are given at points between the circular cone and the corresponding attached bow shock wave. Also some overall quantities such as normal and axial force coefficients are listed. Results are given for Mach numbers ranging from 1.5 to 20, for cone half angles from 5 deg to 40 deg and for successive values of relative incidence 0, 0.1, 0.2 ...... (Author)

Descriptors :   (*CONICAL BODIES, *SUPERSONIC FLOW), ANGLE OF ATTACK, VELOCITY, DENSITY, PRESSURE, SHOCK WAVES, FORCE(MECHANICS), TABLES(DATA), CANADA

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE