Accession Number:

AD0630780

Title:

ON THE USE OF THE SHOCK LAYER APPROXIMATION IN THE INVERSE HYPERSONIC BLUNT BODY PROBLEM,

Descriptive Note:

Corporate Author:

DOUGLAS AIRCRAFT CO INC SANTA MONICA CALIF MISSILE AND SPACE SYSTEMS DIV

Personal Author(s):

Report Date:

1965-10-01

Pagination or Media Count:

59.0

Abstract:

The usefulness of the shock-layer approximation as a method of attack to the hypersonic blunt body problem is studied. Mainly the inverse problems of axisymmetric inviscid flow of a calorically perfect gas in which the shock geometry is given are discussed. Methods which are consistent with approximations based on a high shock compression ratio but modified to take into account the contribution of the tangential pressure gradient and some other second order terms are proposed. Good agreement in body shape and streamlines with other more exact numerical solutions is shown not only for specific heat ratios as high as gamma 53 and 2, but also for stagnation regions of very blunt configurations, for which the standard shock-layer theory completely fails. Analytic forms of the pressure field, body and streamline geometries are developed for the sonic family shocks of arbitrary degree of oblateness and eccentricity in stagnation regions. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE