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- W22485280 abstract "This chapter develops the foundation of inviscid nonlinear shock-expansion theory on pointed bodies in supersonic flows. Fundamental equations of shock and expansion waves are derived and discussed. To extend the analysis to three-dimensional bodies, conical shock theory is derived. Examples from diamond and bi-convex airfoils are used to highlight the shock-expansion techniques in developing lift and wave drag on two-dimensional pointed bodies. Drag polar and the aerodynamic performance parameter, ((L/D)_{text {max}}) are discussed. Axisymmetric and slender bodies are the basis of 3-D shock-expansion application. Approximate methods based on the method of local cones is introduced to estimate the effect of 3-D expansion, using conical shocks associated with smaller nose angle. The problem of asymmetrical flows is analyzed through the method of local cones. The shock-expansion theory is extended to the upper transonic regime. Here, the principle of stationary local Mach numbers near sonic freestream flow is demonstrated and applied to wave drag of axisymmetric bodies at sonic speed. This chapter contains 9 examples and 42 practice problems at the end of the chapter." @default.
- W22485280 created "2016-06-24" @default.
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- W22485280 date "2015-01-01" @default.
- W22485280 modified "2023-09-27" @default.
- W22485280 title "Shock-Expansion Theory" @default.
- W22485280 cites W2063364940 @default.
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- W22485280 doi "https://doi.org/10.1007/978-94-017-9747-4_4" @default.
- W22485280 hasPublicationYear "2015" @default.
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