Loading...
Please wait, while we are loading the content...
Similar Documents
Supersonic flow calculation using a reynolds-stress and an eddy thermal diffusivity turbulence model
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sommer, T. P. So, R. M. C. Zhang, H. S. |
| Copyright Year | 1993 |
| Description | A second-order model for the velocity field and a two-equation model for the temperature field are used to calculate supersonic boundary layers assuming negligible real gas effects. The modeled equations are formulated on the basis of an incompressible assumption and then extended to supersonic flows by invoking Morkovin's hypothesis, which proposes that compressibility effects are completely accounted for by mean density variations alone. In order to calculate the near-wall flow accurately, correction functions are proposed to render the modeled equations asymptotically consistent with the behavior of the exact equations near a wall and, at the same time, display the proper dependence on the molecular Prandtl number. Thus formulated, the near-wall second order turbulence model for heat transfer is applicable to supersonic flows with different Prandtl numbers. The model is validated against flows with different Prandtl numbers and supersonic flows with free-stream Mach numbers as high as 10 and wall temperature ratios as low as 0.3. Among the flow cases considered, the momentum thickness Reynolds number varies from approximately 4,000 to approximately 21,000. Good correlation with measurements of mean velocity, temperature, and its variance is obtained. Discernible improvements in the law-of-the-wall are observed, especially in the range where the big-law applies. |
| File Size | 1382285 |
| Page Count | 42 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930019970 |
| Archival Resource Key | ark:/13960/t6xw9bh8x |
| Language | English |
| Publisher Date | 1993-06-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Supersonic Flow Temperature Distribution Reynolds Number Real Gases Thermal Diffusivity Velocity Distribution Supersonic Boundary Layers Wall Temperature Prandtl Number Compressibility Effects Temperature Ratio Vortices Turbulence Models Wall Flow Heat Transfer Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
