Accession Number : ADB063654


Title :   Aerodynamics of Supersonic Lifting Bodies


Descriptive Note : Final rept. Oct 1977-Sep 1980


Corporate Author : OKLAHOMA UNIV NORMAN SCHOOL OF AEROSPACE MECHANICAL AND NUCLEAR ENGINEERING


Personal Author(s) : Jischke, M C ; Rasmussen, M L


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/b063654.pdf


Report Date : Feb 1981


Pagination or Media Count : 417


Abstract : This report describes a combined theoretical and experimental program of research in the aerodynamics of supersonic lifting bodies. Analytical perturbation techniques are used to study the supersonic flow past slightly elliptical cones, cones whose cross-sections deviate slightly but arbitrarily from that of a right circular cone, cones of small longitudinal curvature, and right circular cones undergoing small harmonic pitching and/or plunging motions. These studies all involve perturbations of the well-known solution for supersonic flow past a right circular cone. Closed-form analytical results are achieved through the use of an approximation that accurately predicts results over the entire range of the hypersonic similarity parameter. These results give hypersonic limiting solutions that agree well with other independent analyses and, at the same time, agree exactly with linearized theory in the linear theory limit. Comparisons with experiment, where possible, also show good agreement.


Descriptors :   *SUPERSONIC CHARACTERISTICS , *HYPERSONIC FLOW , *LIFTING BODIES , MANEUVERABILITY , PITCH(MOTION) , SHOCK WAVES , THEORY , FLOW VISUALIZATION , CURVATURE , APPROXIMATION(MATHEMATICS) , WIND TUNNEL TESTS , AXISYMMETRIC , PERTURBATIONS , MACH NUMBER , HIGH LIFT , SUPERSONIC FLOW , INVISCID FLOW , CONICAL BODIES , BLUNT BODIES , BOUNDARY LAYER FLOW , STEADY FLOW , LIFT TO DRAG RATIO


Subject Categories : Aerodynamics
      Spacecraft Trajectories and Reentry


Distribution Statement : APPROVED FOR PUBLIC RELEASE