NASA NTRS · 19750058122
High Reynolds number transonic flow simulation
Abstract
A code has been developed for simulating high Reynolds number transonic flow fields of arbitrary configuration. An explicit finite-difference method with time splitting is used to solve the time-dependent equations for compressible turbulent flow. A nonorthogonal computational mesh of arbitrary configuration facilitates the description of the flow field. The code is applied to simulate the flow over a two-dimensional 18 percent thick circular-arc biconvex airfoil at zero angle of attack for several different Reynolds numbers and a free-stream Mach number of 0.775.
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Deiwert, G. S.. 1975-01-01. High Reynolds number transonic flow simulation. https://ntrs.nasa.gov/citations/19750058122
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