Accession Number:

AD0763762

Title:

Pressure Fields over Hypersonic Wing-Bodies at Moderate Incidence,

Descriptive Note:

Corporate Author:

ROCKWELL INTERNATIONAL CORP THOUSAND OAKS CALIF SCIENCE CENTER

Personal Author(s):

Report Date:

1972-09-26

Pagination or Media Count:

44.0

Abstract:

Delta wings with conically subsonic cone-bodies mounted on their compressive side are analyzed in the hypersonic small disturbance regime. The weakly three dimensional conditions associated with slender parabolic Mach cones are used to validate a linearized rotational approximation of the flow field. A combined integral-series representation is obtained for the pressure distribution between the wing-body and shock wave for arbitrary body cross sections, and is specialized to give analytical formulae for arbitrary order polynomial transversal contours. Numerical results are presented for wedge, parabolic, and higher order cross sections illustrating the dominant character of the cross-flow stagnation singularity associated with sharp wing-body intersections having a finite slope discontinuity. Modified author abstract

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE