Applications of Algebraic Reynolds Stress Turbulence Models Part 2: Transonic Shock-Separated Afterbody

The ability of the three-dimensional Navier – Stokes method PAB3D code to simulate the effect of Reynolds number variation using nonlinear explicit algebraic Reynolds stress turbulence modeling was assessed. Surface pressure coefŽ cient distributions and integrated drag predictions on an axisymmetric nozzle afterbody were compared with experimental data at Reynolds numbers from 10 to 130 3 10. There was generally good agreement of surface static pressure coefŽ cients between the computational  uid dynamics (CFD) and measurement. The change in pressure coefŽ cient distributions with varying Reynolds number was similar to the experimental data trends, though the CFD slightly overpredicted the effect. The computational sensitivity of viscous modeling and turbulence modeling are shown. Integrated afterbody pressure drag was typically slightly lower than the experimental data. The change in afterbody pressure drag with Reynolds number was small, both experimentally and computationally, even though the shape of the distribution was somewhat modiŽ ed with the Reynolds number.