Reduction of the Boundary Layer Thickness in a Hypersonic Nozzle
| Author | : Serge A. Waiter |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1960 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Reduction Of The Boundary Layer Thickness In A Hypersonic Nozzle
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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.
A Boundary Layer Study on Hypersonic Nozzles
| Author | : Paul Joseph Shall (Jr) |
| Publisher | : |
| Total Pages | : 78 |
| Release | : 1968 |
| Genre | : |
| ISBN | : |
An experimental investigation was made to determine the structure and integrated properties of turbulent boundary layers in hypersonic nozzles, at Mach numbers between 10 and 12. It is concluded that the 1/7-power velocity profile does not agree with the experimental data in this Mach number range. However, a velocity profile based on the Crocco energy relations agrees well with the data as does the corresponding temperature profile, except at the point of maximum temperature. The semi-empirical relationships for boundary layer thickness and displacement thickness, proposed by Burke are strongly supported by the experimental data of this study. (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.
Approximate Turbulent Boundary-layer Development in Plane Compressible Flow Along Thermally Insulated Surfaces with Application to Supersonic-tunnel Contour Correction
| Author | : Maurice Tucker |
| Publisher | : |
| Total Pages | : 86 |
| Release | : 1950 |
| Genre | : Air flow |
| ISBN | : |
As an application of the method, the contour correction of supersonic nozzles for the effects of boundary-layer development is discussed from the requirement of continuity of mass flow and from the requirement of expansion- and shock-wave elimination.
Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects
| Author | : Ralph C. Tolle |
| Publisher | : |
| Total Pages | : 274 |
| Release | : 1996 |
| Genre | : Hypersonic wind tunnels |
| ISBN | : |
Low-Density Boundary-Layer Modulation by Suction in a Hypersonic Nozzle
| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1972 |
| Genre | : |
| 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. (Author).
Investigation of a Thick Laminar Boundary Layer in a Supersonic Nozzle
| Author | : Donald Eckhart Emerson |
| Publisher | : |
| Total Pages | : 246 |
| Release | : 1951 |
| Genre | : Ultrasonic waves |
| ISBN | : |
A Method of Calculating Boundary-layer Thickness in Axisymmetric Nozzles with Laminar Hypersonic Flow
| Author | : Arlo F. Johnson |
| Publisher | : |
| Total Pages | : 26 |
| Release | : 1959 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
The excellent agreement between measured boundary layer thickness and thickness calculated by Sivells and Payne recommends their method for calculating turbulent boundary layer growth in axisymmetric hypersonic nozzles. It was thought worthwhile to adapt their approach to the laminar boundary layer. This analysis, along with a limited amount of corroborating data, is presented herein.
