Feasibility of combining linear theory and impact theory methods for the analysis and design of high speed configurations
D. Brooke, D. V. Vondrasek, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, McDonnell Douglas Corporation, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Service, 1979 - Aerodynamics, Transonic - 37 pages
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3.5 Span Station 4.6 Span Station a(CL LT ABASE Ames All-Body Model angle of attack base area camber slope CL LT closed form expressions CLOSED FORM PREDICTIONS combination of linear combined impact theory/linear Data NASA TND Delta Wings DISTRIBUTION ON 76 drag Gentry alone TW/PM Gentry program high Mach numbers high speed configurations Hypersonic impact pressure Impact Theory Methods inverse design mode inverse design procedure INVERTED MATRIX j-th panel leading edge Legend lifting pressure linear theory influence Mach 2.3 Span Mach 4.6 Span Mach angle Mach cone Mach range oblique shock planform Prandtl-Meyer relations PRESSURE DIFFERENCES PRESSURE DISTRIBUTION pressure options region of influence Span Station y/b/2 Sref Swept Flat Plate SWEPT WING Mach theory and impact theory influence coefficients thickness slope thickness terms tions UNCAMBERED CONFIGURATIONS wing camber WING Mach 2.3 Woodward alone Gentry/Woodward Woodward program x/c x/c x/c FIGURE Xref