Effect Of Heating And Cooling Strips On Boundary Layer Stability Of Nozzles And Test Sections Of Supersonic Wind Tunnels
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Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 60 |
Release | : 2018-07-16 |
Genre | : |
ISBN | : 9781722791766 |
The objective of the research is to understand supersonic laminar flow stability, transition, and active control. Some prediction techniques will be developed or modified to analyze laminar flow stability. The effects of supersonic laminar flow with distributed heating and cooling on active control will be studied. The primary tasks of the research applying to the NASA/Ames Proof of Concept (POC) Supersonic Wind Tunnel and Laminar Flow Supersonic Wind Tunnel (LFSWT) nozzle design with laminar flow control are as follows: (1) predictions of supersonic laminar boundary layer stability and transition, (2) effects of wall heating and cooling for supersonic laminar flow control, and (3) performance evaluation of POC and LFSWT nozzles design with wall heating and cooling effects applying at different locations and various length. Lo, Ching F. Unspecified Center...
Author | : William Scott Meredith |
Publisher | : |
Total Pages | : 94 |
Release | : 1994 |
Genre | : Boundary layer |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 538 |
Release | : 1995 |
Genre | : Aeronautics |
ISBN | : |
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author | : W. Pfenninger |
Publisher | : |
Total Pages | : 312 |
Release | : 1974 |
Genre | : Boundary layer |
ISBN | : |
Author | : Martin Sichel |
Publisher | : |
Total Pages | : 84 |
Release | : 1963 |
Genre | : |
ISBN | : |
Author | : Fang-Jenq Chen |
Publisher | : |
Total Pages | : 60 |
Release | : 1984 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : E. R. Van Driest |
Publisher | : |
Total Pages | : 108 |
Release | : 1961 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.
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.
Author | : R. J. Volluz |
Publisher | : |
Total Pages | : 512 |
Release | : 1961 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Jackson R. Stalder |
Publisher | : |
Total Pages | : 86 |
Release | : 1960 |
Genre | : Heat |
ISBN | : |