
Accession Number : AD0287425
Title : UNIFORMLY VALID SECONDORDER 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 : Secondorder supersonic flow over a cruciform configuration is sudied for supersonic inlets, wingbody junctions and vehicle fins. Severe local failures are identified and adjusted for the ordinary secondorder 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. secondorder solution uniformly valid to first order is constructed by adjustment of the ordinary secondorder 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 vertexcentered 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 vertexcentered undisturbed Mach cone. Results are given for the case of two iAD287 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