Accession Number : AD0287425

Title :   UNIFORMLY VALID SECOND-ORDER SOLUTION FOR SUPERSONIC FLOW OVER CRUCIFORM SURFACES

Corporate Author : JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB

Personal Author(s) : WALLACE,JAMES JR. ; CLARKE,JOSEPH H.

Report Date : JUN 1962

Pagination or Media Count : 24

Abstract : Second-order supersonic flow over a cruciform configuration is sudied for supersonic inlets, wing-body junctions and vehicle fins. Severe local failures are identified and adjusted for the ordinary second-order theory. For wings with discontinuous slopes, discontinuous potentials occur across the planar shock and squareroot singularities in the velocities occur at the intersection of these shocks with the ruciform surfaces. second-order solution uniformly valid to first order is constructed by adjustment of the ordinary second-order solution obtained first. The uniformly valid solution has two different series representations in the thickness parameter. This solution gives the detailed wave structure and shows a flow regime upstream of the vertex-centered undisturbed Mach cone not predicted by the ordinary theory. The wave structure consists of a pyramidal arrangement of planar shocks adjacent to and upstream of the above cone, followed by weaker oblique expansion fans and finally by two extremely weak shocks coincident with the vertex-centered undisturbed Mach cone. Results are given for the case of two iAD-287 426Div. 9 U (TITA/SEB) Bell Aerosystems Co., Buffalo, N. Y. THERMOELASTIC EFFECTS ON HYPERSONIC STABILITY AND CONTROL. PART II. VOLUME I. ELASTIC RESPONSE DETERINATIONS FOR SEVERELY HEATED WINGS. Final rept., by Richard H. Gllagher and Rolland D. Huff. Aug 62, 160p. incl. illus. tersecting wedges. (uthor)

Descriptors :   *CRUCIFORM WINGS, *SUPERSONIC FLOW, AERODYNAMIC CONFIGURATIONS, DUCT INLETS, EQUATIONS, FINS, JET ENGINE INLETS, THEORY, VORTICES, WING BODY CONFIGURATIONS, WING INLETS

Distribution Statement : APPROVED FOR PUBLIC RELEASE