Accession Number : AD0691270

Title :   A NUMERICAL METHOD FOR CALCULATING STEADY UNSYMMETRICAL SUPERSONIC FLOW PAST CONES.

Descriptive Note : Technical rept.,

Corporate Author : CALIFORNIA UNIV BERKELEY DIV OF AERONAUTICAL SCIENCES

Personal Author(s) : Ndefo,D. Ejike

Report Date : MAY 1969

Pagination or Media Count : 88

Abstract : Telenin's numerical method is adapted to the problem of steady supersonic flow past pointed conical bodies at yaw. The method is formulated for cones of circular cross-sections with the intention of determining bounded analytic solutions uniformly valid in the region between the shock and cone surfaces. Attention is focused on the nature of the entropy field and the behavior of the streamlines as influenced by variations in the free-stream conditions. As an example, numerical computations are carried out for flow past a circular cone of semi-apex angle 20 deg yawed at angles of attack varying from 0 to 20 deg with respect to a free-stream of Mach number 3.53. Solutions are compared with experimental results and with solutions based on other numerical methods. The solutions confirm the existence of a vortical singularity at the leeward generator of the cone, but no evidence is found of the 'lift-off' of this singularity as suggested by Ferri. The entropy layer is shown to be very thin at small angles of attack but relatively thick at large angles of attack. The directions from which the streamlines enter the vortical singularity are found to depend on the angle of attack. (Author)

Descriptors :   (*CONICAL BODIES, SUPERSONIC CHARACTERISTICS), NUMERICAL ANALYSIS, STABILITY, YAW, VORTICES, ENTROPY, ANGLE OF ATTACK

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE