The integral matrix procedure is used to accurately and efficiently compute nonsimilar hypersonic laminar boundary layer equations of perfect gas and equilibrium air around the axisymmetric reentry configurations. The boundary layer equations are employed to efficiently compute the flowfield for the afterbody region by using a space marching technique. Using the integral matrix procedure able us to create accurate and smooth results using the minimum grid in the boundary layer and minimize the computational costs. This algorithm is highly appropriate to design of hypersonic reentry vehicles. Comparisons of the results with experimental data have demonstrated that accurate solutions are obtained.
Integral matrix procedure for laminar boundary layer flow over axisymmetric bodies with real gas effects
2013-06-01
1669676 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
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