6 pages matching values behind shock in this book
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afterbody angle-of-attack angles of attack Aomponents in Aombination approximate method aspect ratios 3/8 B2 and B2W2 based on body BjWi body axis body length body-wing boundary-layer flow calculated center cone combinations were obtained data and force directional stability downstream drag coefficient dynamic pressure effects engine nacelle combinations experimental Figure 29 Filled symbols denote fineness ratio flow field Flow survey flow-field characteristics free-stream Mach number increment inlet location left outboard Leland H lift coefficient Mach line maximum lift-drag ratio model B2W2 NACA TN nacelle location NASA TN X-lll negative angles nose apex nose shock obtained at angles orifices outboard plane outboard vertical planes percent pitot pitot-pressure ratio plane of symmetry presented in figure Reynolds number Right outboard Rlow-field data shock expansion method shock-wave shown sideslip angle slender-body theory straight-through duct Supersonic symbols denote values tunnel values behind shock vortex Wave Drags windward side Wing-Body Combinations yawing yawing-moment coefficients