Integral solution of compressible turbulent boundary layers using improved velocity profiles /
David L. Whitfield.
Description
- Language(s)
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English
- Published
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Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, 1978.
- Summary
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A shear-work integral method is developed for calculating compressible turbulent boundary layers on planar or axisymmetric bodies. This method differs from other integral techniques primarily in the velocity profile and the velocity-temperature relation used. The velocity profile is an analytical expression that depends on the local values of skin friction, shape factor, and Reynolds number based on momentum thickness, thus no new parameters not already occurring in the integral equations are introduced. The velocity- temperature relation is also an analytical expression that describes the total- temperature overshoot near the outer edge of turbulent adiabatic wall boundary layers with nonunity Prandtl number and recovery factor. The method is fast, easy to use, and shown to provide good agreement with experimental data. The resulting computer code is relatively small. A computer program listing that is applicable to the calculation of impermeable, adiabatic wall, turbulent boundary layers for Mach numbers up to three is included.
- Note
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"December 1978."
"Final Report: March -- November 1977."
- Physical Description
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47 pages :
illustrations ;
28 cm
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