Integral Matrix Procedure for Laminar Boundary Layer Flow over Axisymmetric Bodies with Real Gas Effects

The integral matrix procedure is used to accurately and efficiently compute nonsimilarhypersonic laminar boundary layer equations of perfect gas and equilibrium air around theaxisymmetric reentry configurations. The boundary layer equations are employed toefficiently compute the flowfield for the afterbody region by using a space marchingtechnique. Using the integral matrix procedure able us to create accurate and smooth resultsusing the minimum grid in the boundary layer and minimize the computational costs. Thisalgorithm is highly appropriate to design of hypersonic reentry vehicles. Comparisons of theresults with experimental data have demonstrated that accurate solutions are obtained.

کلیدواژه ها:

Hypersonic Flow ، Equilibrium Air ، Boundary Layer ، Integral Method