Pressure Fields over Hypersonic Wing-Bodies at Moderate Incidence,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 26, 1972
- Accession Number
- AD0763762
Entities
People
- N. Malmuth