Turbulent Boundary Layer Heat Transfer And Transition Measurements With Surface Cooling At Mach 6
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A Review of High-speed, Convective, Heat-transfer Computation Methods
Author | : Michael E. Tauber |
Publisher | : |
Total Pages | : 44 |
Release | : 1989 |
Genre | : Aerodynamic heating |
ISBN | : |
Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0
Author | : Victor Zakkay |
Publisher | : |
Total Pages | : 86 |
Release | : 1962 |
Genre | : Boundary layer |
ISBN | : |
A modified equation for the heat transfer coefficient in the transitional and fully turbulent region based on the F.P.R.E. method is then presented. This method gives good agreement with the experimental results presented here.
Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer
Author | : Robert L. P. Voisinet |
Publisher | : |
Total Pages | : 128 |
Release | : 1972 |
Genre | : Heat |
ISBN | : |
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a zero-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall for a nominal Mach number of 4.9, at momentum thickness Reynolds numbers from 7,000. to 58,000. and at wall-to-adiabatic-wall temperature ratios of 1.0, 0.8 and 0.25. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. Furthermore, the wall shear and surface heat transfer were measured directly with a skin-friction balance and a heat-transfer gage, respectively. (Author Modified Abstract).