Measurements Of A Mach 49 Zero Pressure Gradient Turbulent Boundary Layer With Heat Yransfer
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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).
Author | : Robert L. P. Voisinet |
Publisher | : |
Total Pages | : 105 |
Release | : 1972 |
Genre | : |
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).
Author | : Roger L. Kimmel |
Publisher | : |
Total Pages | : 46 |
Release | : 1993 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Boundary layer transition was measured in zero, favorable, and adverse pressure gradients at Mach 8 using heat transfer. Models consisted of 7 degrees half angle forecones 0.4826 m long, followed by flared or ogive aft bodies 0.5334 m long. The flares and ogives produced constant pressure gradients. For the cases examined, favorable pressure gradients delay transition and adverse pressure gradients promote transition, but transition zone lengths are shorter in favorable pressure gradient. Results of the effect of adverse pressure gradient on transition zone lengths were inconclusive.
Author | : |
Publisher | : |
Total Pages | : 89 |
Release | : 1969 |
Genre | : |
ISBN | : |
The results of a detailed experimental investigation of a two- dimensional turbulent boundary layer at zero-pressure gradient are presented. The studies were made at the free-stream Mach number of 5, momentum-thickness Reynolds number from 4800 to 56,000 and wall-to-adiabatic-wall temperature ratios from 0.5 to 1.0. The data are in analytical terms of velocity profile, temperature profile, law-of-the-wall, velocity-defect law and incompressible form factor. Comparisons of local skin-friction coefficients obtained by four different experimental methods are shown. An empirical equation was derived from the shear-balance data to calculate the friction coefficient from known values of Mach number, heat transfer and Reynolds number.
Author | : Ivan E. Beckwith |
Publisher | : |
Total Pages | : 100 |
Release | : 1971 |
Genre | : Heat |
ISBN | : |
Measurements of total temperature and pitot pressure across boundary layer of test section wall of axisymmetric contoured nozzle at hypersonic speed in nitrogen.
Author | : C. Economos |
Publisher | : |
Total Pages | : 84 |
Release | : 1971 |
Genre | : |
ISBN | : |
Author | : Mitchel H. Bertram |
Publisher | : |
Total Pages | : 44 |
Release | : 1959 |
Genre | : |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 132 |
Release | : 1970 |
Genre | : |
ISBN | : |
Author | : Richard D. Samuels |
Publisher | : |
Total Pages | : 82 |
Release | : 1967 |
Genre | : Skim friction (Aerodynamics) |
ISBN | : |
Author | : David L. Whitfield |
Publisher | : |
Total Pages | : 108 |
Release | : 1976 |
Genre | : Laminar boundary layer |
ISBN | : |
This report describes the results of analytical, numerical, and experimental investigations of incompressible and compressible boundary layers. The subjects considered are (1) Laminar and/or turbulent numerical boundary-layer calculations in which the Reynolds stress is related to the turbulent kinetic energy; (2) an analytical investigation of turbulence near a wall which is not founded on classical mixing-length theory; (3) analytical solutions for relating velocity and temperature throughout turbulent boundary layers for nonunity Prandtl numbers; (4) a description of the data reduction of pitot pressure measurements utilizing these analytical results, and (5) the application of the numerical and analytical results to the analysis of turbulent boundary-layer measurements made in the Propulsion Wind Tunnel Facility (PWT).