Accession Number:

ADA023264

Title:

Supersonic Flow about Cones at Large Angles of Attack.

Descriptive Note:

Interim rept.,

Corporate Author:

CALIFORNIA UNIV BERKELEY DEPT OF MECHANICAL ENGINEERING

Personal Author(s):

Report Date:

1974-05-01

Pagination or Media Count:

133.0

Abstract:

A numerical method is presented which is applicable to the supersonic inviscid flow about cones inclined at such angles of attack that a substantial region of supersonic crossflow exists M sub cr 1. The method is based partly on the method of Gilinskii, Telenin and Tinyakov and partly on the method of characteristics. The method produces results that compare favorably with experimental data and with the results of other numerical methods. The numerical method has produced results in the range free stream Mach number 3 to 16 incidence, alpha 10 to 50 deg, nose cone angles, theta sub b 5 to 30 deg. These results demonstrate similar trends with free stream Mach number, alpha and theta sub b as obtained for subsonic crossflow Mach numbers m sub cr 1 by Babenko et al BVLR method. From the numerical data and from the equations of motion at the body surface it appears that the vortical singularity will remain attached to the body if the crossflow remain subsonic. If the crossflow is just supersonic no internal shock will occur and if, in addition, theta sub b is small the vortical singularity will be situated just above the body surface. For larger M sub cr the supersonic crossflow region is terminated by an internal shock and the vortical signularity occurs further from the body.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE