Calculation of Viscous Hypersonic Flow over a Severely Indented Nosetip

A numerical procedure for computing viscous hypersonic flows over severely indented nosetips is described. The computer code has been satisfactorily verified for the cases of laminar flow over a hemisphere cylinder with an adiabatic wall at Mach 3 and a sphere cone with an isothermal wall at Mach 6. It is also demonstrated that the code can compute both laminar and turbulent flowfields for a severely indented nosetip with a large separation bubble. Numerical results are presented and compared to experimental data for surface pressure, shock shape, density and velocity fields, and heat transfer in terms of Stanton number.