Gas-surface interaction effect on round leading edge aerothermodynamics

effects of incomplete surface accommodation in rarefied gas flow have been studied by using the direct simulation monte carlo (dsmc) method in conjunction with the cercignani-lampis-lord gas surface interaction model. the dsmc calculations examine differences in predictions of aerodynamic forces and heat transfer between full and partial surface accommodation for hypersonic flow past round leading edges at zero incidence. the aerodynamic performance of round leading edges is assessed by using the heat transfer rate, the total drag and the shock wave standoff distance. twenty-five combinations of nose radius, normal and tangential accommodation coefficients were used in the simulation. for the flow conditions considered, the analysis showed that stagnation point heating, total drag and shock standoff distance are sensitive to changes on either the normal or tangential accommodation coefficient. the results substantiate that it becomes imperative to take surface accommodation into account in order to make accurate predictions of the aerodynamic forces on, and heat transfer rates to, bodies in rarefied hypersonic flow.