Effects Of Number
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Effects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate
Author | : Don W. Jillie |
Publisher | : |
Total Pages | : 36 |
Release | : 1961 |
Genre | : Fluid mechanics |
ISBN | : |
Effects of Unit Reynolds Number, Nose Bluntness, and Roughness on Boundary Layer Transition
Author | : J. Leith Potter |
Publisher | : |
Total Pages | : 166 |
Release | : 1960 |
Genre | : Boundary layer |
ISBN | : |
Condtions encountered in the high Mach number flow regime are show to profoundly affect the longitudinal extent of the boundary layer from beginning to end of transition, the distribution of fluctuation energy in the laminar layer, and effectiveness of surface roughness in promoting transition. A critical layer of intense local energy fluctuations was found at all Mach numbers studied. The existence of such a critical layer is predicted by stability theory. Hot-wire surveys of the laminar, transitional, and turbulent boundary layers are presented to illustrate the critical layer in laminar flow and subsequent development into the transition process. The relation between boundary layer transition on flat plates and cones in supersonic flow is explored and a process for correcting data to account for leading edge bluntness is devised. On the basis of a comparison of data corrected for the effects of leading edge geometry, it is shown that the Reynolds umber of transition on a cone is three times that on a vanishingly thin flate plate. Close agreement between data from various wind tunnels is demonstrated. Study of the effect of finite leading edges yields significant illustrations of the influence of unit Reynolds number on boundary layer transition. A correlation of the effects of surface roughness on transition is achieved. This treatment includes two- and three-dimensional roughness in both subsonic and supersonic streams. At this time only zero pressure gradients have been studied. The entire range of movement of transition from its position with no roughness up to its reaching the roughness element is describable by the procedure give. Examples of application of the correlation results show excellent agreement with experimental data from a variety of sources. Implications concerning tripping hypersonic boundary layers are discussed.
Investigation of the Effects of Low Reynolds Number Operation on the Performance of a Single-Stage Turbine with a Downstream Stator
Author | : Robert E. Forrette |
Publisher | : |
Total Pages | : 52 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Effects of Mach Number and Wall-temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5
Author | : Thorval Tendeland |
Publisher | : |
Total Pages | : 28 |
Release | : 1959 |
Genre | : Aerodynamic heating |
ISBN | : |
The heat-transfer data obtained from the model were found to correlate when the T' method of Sommer and Short was used. The increase in turbulent heat-transfer rate with a reduction in wall to free-stream temperature ratio was of the same order of magnitude as has been found for the turbulent skin-friction coefficient.
Effects of Reynolds Number and Flow Incidence on the Force Characteristics of a Family of Flat-front Cylinders
Author | : Vernard E. Lockwood |
Publisher | : |
Total Pages | : 50 |
Release | : 1967 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Investigation of the Effects of Model Scale and Stream Reynolds Number on the Aerodynamic Characteristics of Two Rectangular Wings at Supersonic Speeds on the Langley 9-inch Supersonic Tunnel
Author | : Donald E. Coletti |
Publisher | : |
Total Pages | : 36 |
Release | : 1955 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Effects of Subsonic Mach Number on the Forces and Pressure Distributions on Four NACA 64A-series Airfoil Sections at Angles of Attack as High as 28 Degrees
Author | : Louis S. Stivers |
Publisher | : |
Total Pages | : 676 |
Release | : 1954 |
Genre | : Aerodynamic load |
ISBN | : |
A region of slight compression, heretofore undescribed, was established within the local supersonic region on each of the airfoil sections near the leading edge in place of an expected expansion. This leading edge compression region was formed just downstream of the abrupt.
Evaluation of Reynolds Number and Tunnel Wall Porosity Effects on Nozzle Afterbody Drag at Transonic Mach Numbers
Author | : C. E. Robinson |
Publisher | : |
Total Pages | : 38 |
Release | : 1976 |
Genre | : Aerodynamics, Transonic |
ISBN | : |
An experimental investigation was conducted to study the effects of Reynolds number variation on isolated nozzle afterbody performance. A strut-mounted cone-cylinder model with three separate afterbody configurations for Aerospace Research and Development (AGARD) was used for this investigation. This program was conducted in two phases distinguished by the model size and the wind tunnels used to obtain the experimental results. The effect of tunnel wall porosity on nozzle afterbody (NAB) performance was investigated.