Turbulence modeling of shock separated boundary-layer flowsComputations of transonic and hypersonic shock-separated boundary-layer flows using zero-equation (algebraic), one-equation (kinetic energy), and two-equation (kinetic energy plus length scale) turbulence eddy viscosity models are described and compared with measurements. The computations make use of a new Navier-Stokes computer algorithm that has reduced computing times by one to two orders of magnitude. The algorithm, and how the turbulence models are incorporated into it, are described. Results for the transonic flow show that the unmodified one-equation model is superior to the zero-equation model in skin-friction predictions. For the hypersonic flow, a highly modified one-equation model that accurately predicts surface pressure and heat transfer is described. Preliminary two-equation model results are also presented.
Document ID
19770051014
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Coakley, T. J. (NASA Headquarters Washington, DC United States)
Viegas, J. R. (NASA Ames Research Center Moffett Field, Calif., United States)