Krishnan, V and Mathur, NB (1997) Afterbody Boundary Layer Measurements in the Base Flow Facility. Technical Report. National Aerospace Laboratories, Bangalore,India.
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Abstract
Experiments were conducted to study the boundary layer properties on a cylindrical afterbody model in the Base Flow Facility. Measurements were made using a boundary layer pitot rake in the freestream Mach number range of 0.5 to 3.0. The ratio of the boundary layer thickness to the model diameter decreased from 6.5% to 2.5% in the above Mach number range. The mean velocity profiles showed that the boundary layer is turbulent and has features typical of a zero pressure gradient compressible turbulent boundary layer. The velocity profiles plotted in the wall-law co-ordinates show the existence of the logarithmic region with values of slope and intercept of 5.62 and 4.7 respectively.
| Item Type: | Proj.Doc/Technical Report (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Aftrbody;Compressible Turbulent Boundary Layer;Base Flow Facility |
| Subjects: | AERONAUTICS > Aerodynamics |
| Division/Department: | Experimental Aerodynamics Division, Experimental Aerodynamics Division |
| Depositing User: | Mr. N A |
| Date Deposited: | 10 May 2006 |
| Last Modified: | 24 May 2010 09:41 |
| URI: | http://nal-ir.nal.res.in/id/eprint/1288 |
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