The major aspects of a code for the design of shockless airfoils in two-dimensional transonic flow are reviewed. The code is based on a method of analytic continuation into the domain of two complex characteristic variables, which makes it possible to associate a shockless airfoil with a given pressure distribution. This procedure is compared with another more direct method based on a two-dimensional analysis code that has had wide acceptance by the aircraft industry.
Shockless airfoils for wings, compressors, and turbines
Nonlinear partial differential equations in engineering and applied science ; 1979 ; Kingston, RI
1980-01-01
Miscellaneous
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English