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Self-adaptive difference method for the effective solution of computationally complex problems of boundary layer theory (1986)

Gruening, J. ; Daeubler, H. G. ; Schoenauer, W. ; [et al.]

In: CASI

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Publication Date: 2019-08-27

Description: An implicit difference procedure for the solution of equations for a chemically reacting hypersonic boundary layer is described. Difference forms of arbitrary error order in the x and y coordinate plane were used to derive estimates for discretization error. Computational complexity and time were minimized by the use of this difference method and the iteration of the nonlinear boundary layer equations was regulated by discretization error. Velocity and temperature profiles are presented for Mach 20.14 and Mach 18.5; variables are velocity profiles, temperature profiles, mass flow factor, Stanton number, and friction drag coefficient; three figures include numeric data.

Keywords: FLUID MECHANICS AND HEAT TRANSFER

Type: NASA-TM-88440 , NAS 1.15:88440 , DGLR-76-185 , Sep 14, 1976 - Sep 16, 1976; Munich; Germany

Format: application/pdf

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