## Feasibility of Combining Linear Theory and Impact Theory Methods for the Analysis and Design of High Speed Configurations, Volume 3069National Aeronautics and Space Administration, Scientific and Technical Information Service, 1979 - Aerodynamics, Transonic - 37 pages |

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3.5 Span Station ABASE ALL-BODY MODEL B5 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 Cp 4a D D i iD Data NASA TND Delta Wings DISTRIBUTION ON 76 drag Gentry alone TW/PM Gentry program GENTRY/WOODWARD SOLUTION high Mach numbers high speed configurations Hypersonic ID i i 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 4.6 Span Mach angle Mach cone Mach range oblique shock planform Prandtl-Meyer relations PRESSURE DIFFERENCES PRESSURE DISTRIBUTION region of influence Span Station y/b/2 supersonic Swept Flat Plate SWEPT WING Mach theory and impact theory influence coefficients thickness slope thickness terms UNCAMBERED CONFIGURATIONS unmodified linear theory wing camber WING Mach 2.3 Woodward program x/c x/c FIGURE x/c x/c x/c Xref