
Accession Number : AD0419927
Title : UNIFORM SECONDORDER SOLUTION FOR SUPERSONIC FLOW OVER DELTA WING USING REVERSEFLOW INTEGRAL METHOD,
Corporate Author : BROWN UNIV PROVIDENCE R I
Personal Author(s) : Clarke,Joseph H. ; Wallace,James
Report Date : APR 1963
Pagination or Media Count : 28
Abstract : The problem of supersonic flow over an inclined flatplate delta wing with supersonic edges is solved to second order in incidence. This solution for surface pressure is uniform and fully analytic. The approach utilizes a reverseflow integral method previously developed for secondorder problems. This method is augmented by a number of techniques appropriate to its framework. The simplification over standard techniques acgieved by using these reverseflow methods is quite substantial and makes the problem tractible. Reverseflow procedures give a volumesurface integral relation that connects the secondorder forward flow over the body of interest with the linearized reverseflow over a related body. A singular integral equation is generated from the integral relation by introducing the edge sweep of the reverseflow wing as a free parameter. An inversion is available which gives the secondorder solution on the surface of the wing. The solution is then made uniformly valid using techniques previously developed. (Author)
Descriptors : (*DELTA WINGS, SUPERSONIC FLOW), FLUID FLOW, AERODYNAMIC CHARACTERISTICS, THEORY, VELOCITY, INTEGRAL EQUATIONS, PRESSURE, FLAT PLATE MODELS
Distribution Statement : APPROVED FOR PUBLIC RELEASE