An Experimental Study of Boundary Layer Parameters at the Exit of a Hypersonic Contoured Nozzle
| Author | : James Daryl Cox (1LT, USAF.) |
| Publisher | : |
| Total Pages | : 64 |
| Release | : 1965 |
| Genre | : Boundary layer |
| ISBN | : |
An Experimental Study Of Boundary Layer Parameters At The Exit Of A Hypersonic Contoured Nozzle
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An Experimental Study of Boundary Layer Parameters at the Exit of a Hypersonic Contoured Nozzle
| Author | : James Daryl Cox |
| Publisher | : |
| Total Pages | : 72 |
| Release | : 1965 |
| Genre | : |
| ISBN | : |
The boundary layer thickness and displacement thickness were experimentally evaluated at the exit plane of an arc heated 9.492 inch exit diameter hypervelocity (M> or =8) contoured nozzle for both equilibrium and nonequilibrium flows. It was concluded that the boundary layers were turbulent and the use of a plenum chamber decreases the displacement thickness for identical arc heater stagnation chamber conditions. (Author).
Comparison of Prediction Methods and Studies of Relaxation in Hypersonic Turbulent Nozzle-wall Boundary Layers
| Author | : Dennis M. Bushnell |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1969 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls.
Experimental Study of Nozzle Wall Boundary Layers at Mach Numbers 20 to 47
| Author | : Joseph H. Kemp |
| Publisher | : |
| Total Pages | : 116 |
| Release | : 1972 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
The nozzle wall boundary layer of an M-50 helium tunnel was investigated with pitot pressure, total temperature, skin friction, and wall heat transfer measurements at five stations and hot wire measurements at two stations. The results indicated that the boundary layer was turbulent with a thick viscous sublayer. Pressure gradients were observed across the boundary layer; the effect of these gradients on the equations of motion are discussed. The direct skin friction measurements were higher than expected from empirical predictions; the Reynolds analogy factors however were lower than expected. Hot wire measurements indicated mass flow fluctuations as large as 80 percent of the local mean mass flow at the edge of the viscous sublayer with a maximum value relative to the edge mass flow of about 15 percent at gamma about equal to 0.8.
Low-density Boundary-layer Modulation by Suction in a Hypersonic Nozzle
| Author | : Max Kinslow |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1973 |
| Genre | : Hypersonic wind tunnels |
| ISBN | : |
The potential value of controlled boundary-layer removal from the wall of a nozzle for low-density hypersonic flow was investigated in a brief experimental program. A particular objective was the achievement of sufficient control over boundary-layer thickness to enable a contoured nozzle to be operated under off-design conditions without excessive deterioration of flow uniformity. The nozzle contour was greatly influenced by boundary-layer thickness. Boundary-layer removal involved suction through perforated walls where local nozzle static pressures exceeded the pressure in the large tank which enclosed the nozzle and test section.
Boundary Layer Profile Measurements in Hypersonic Nozzles
| Author | : Norman Ellis Scaggs |
| Publisher | : |
| Total Pages | : 78 |
| Release | : 1965 |
| Genre | : Boundary layer |
| ISBN | : |
An experimental investigation made to determine the flow parameter profiles across the boundary layer on contoured, axisymmetric hypersonic nozzles is described. The pitot pressure and total temperature profiles measured across the boundary layers on nozzles of Mach number seven and twelve are shown in graphical form. The static temperature and velocity profiles, calculated with the assumption of constant static pressure across the boundary layer, are given. A correlation is shown to exist between the exponent of the velocity profile power law and the product of the ratios of wall temperature to free stream total temperature and axial distance to momentum thickness. The static temperature profiles, calculated from the measured data is compared with Crocco's relationship for the static temperature in terms of the velocity profile. (Author).
Boundary Layer Profile Measurements in Hypersonic Nozzles
| Author | : Norman Ellis Scaggs |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1965 |
| Genre | : Boundary layer |
| ISBN | : |
An experimental investigation made to determine the flow parameter profiles across the boundary layer on contoured, axisymmetric hypersonic nozzles is described. The pitot pressure and total temperature profiles measured across the boundary layers on nozzles of Mach number seven and twelve are shown in graphical form. The static temperature and velocity profiles, calculated with the assumption of constant static pressure across the boundary layer, are given. A correlation is shown to exist between the exponent of the velocity profile power law and the product of the ratios of wall temperature to free stream total temperature and axial distance to momentum thickness. The static temperature profiles, calculated from the measured data is compared with Crocco's relationship for the static temperature in terms of the velocity profile. (Author).
