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Calculation of shock-separated turbulent boundary layers
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Baldwin, B. S. Rose, W. C. |
| Copyright Year | 1975 |
| Description | Numerical solutions of the complete, time-averaged conservation equations using several eddy-viscosity models for the Reynolds shear stress to close the equations are compared with experimental measurements in a compressible, turbulent separated flow. An efficient time-splitting, explicit difference scheme was used to solve the two-dimensional conservation equations. The experiment used for comparison was a turbulent boundary layer that was separated by an incident shock wave in a Mach 2.93 flow with a unit Reynolds number of 5.7 x 10 to the seventh power m. Comparisons of predicted and experimental values of surface pressure, shear stress along the wall, and velocity profiles are shown. One of the tested eddy-viscosity models which allows the shear stress to be out of equilibrium with the mean flow produces substantially better agreement with the experimental measurements than the simpler models. A tool is thereby provided for inferring additional information about the flow, such as static pressures in the stream, which might not be directly obtainable from experiments. |
| File Size | 655399 |
| Page Count | 17 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760002932 |
| Archival Resource Key | ark:/13960/t7kq2sc2d |
| Language | English |
| Publisher Date | 1975-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Turbulent Boundary Layer Shear Stress Shock Wave Interaction Separated Flow Prediction Analysis Techniques Boundary Layer Equations Compressible Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
