2 edition of Downstream influence of swept slot injection in hypersonic turbulent flow found in the catalog.
Downstream influence of swept slot injection in hypersonic turbulent flow
Jerry N Hefner
by National Aeronautics and Space Administration, for sale by the National Technical Information Service in Washington, Springfield, Va
Written in English
|Statement||Jerry N. Hefner, Aubrey M. Cary, Jr. and Dennis M. Bushnell ; Langley Research Center|
|Series||NASA technical note ; NASA TN D-8506, NASA technical note -- NASA TN D-8506|
|Contributions||Carey, Aubrey M , joint author, Bushnell, Dennis M., joint author, United States. National Aeronautics and Space Administration, Langley Research Center|
|The Physical Object|
|Pagination||50 p. :|
|Number of Pages||50|
dx Separation in Supersonic-Flow and Free-Interaction Processes 53 a laminar flow Value at separation S x F 1 1 2 3 L / x x x 0 0 Plateau value b turbulent flow x F L / x x x 0 Value at separation 2 Plateau value 3 2 1 4 6 0 S Figure Free-interaction theory. Bulmer (refs. 97 and 98) gives a correlation for turbulent flow base heating on cones in hypersonic flow in the form (Nu/Pr)b ^ ™ ^^^=(Reb/Rec) (67) In equation (67), the subscript b refers to the evaluation at condiuons where the flow has expanded isentropically to the base pressure and the reference length is the base radius.
gential slot injection offers an attractive potential at hypersonic speeds, where both large reductions in skin-friction drag and surface temperatures have been measured. Continu-ing efforts are underway to determine the effect of swept and multiple slots. The simplic-. The influence of wake will maintain through the blade rows far in a downstream direction. Flow, characterized by low velocities, has normal velocity component toward the suction side of the downstream blade, thus an upstream wake with low velocities and higher turbulence levels can move toward the suction side of the blade.
Full text of "Flow control [electronic resource]: fundamentals and practices" See other formats. The influence of wavy wall on the hypersonic boundary layer instability and the related aerodynamic heating are investigated over a flared cone. A length-to-depth six cavity is employed in the experiments with a Mach number of the incoming flow. The upstream injection is generated in the leading edge of the cavity with a large momentum.
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Downstream influence of swept slot injection in hypersonic turbulent flow. Washington: National Aeronautics and Space Administration ; Springfield, Va.: For. Results of an experimental and numerical investigation of tangential swept slot injection into a thick turbulent boundary layer at Mach 6 are presented.
Film cooling effectiveness, skin friction, and flow structure downstream of the swept slot injection were investigated.
The data were compared with that for unswept slots, and it was found that cooling effectiveness and skin friction Cited by: 2. Downstream influence of swept slot injection in hypersonic turbulent flow / By Jerry N. Hefner, joint author. Dennis M. Bushnell, joint author.
Topics: Turbulent boundary layer., Hypersonic planes. DOWNSTREAM INFLUENCE OF SWEPT SLOT INJECTION IN HYPERSONIC TURBULENT FLOW Jerry N. Hefner, Aubrey M. Cary, Jr., and Dennis M.
Bushnell Langley Research Center SUMMARY Results of an experimental and numerical investigation of tangential swept slot injection (sweep angles of O and 45O) into a thick turbulent boundary.
Downstream influence of swept slot injection in hypersonic turbulent flow Results of an experimental and numerical investigation of tangential swept slot injection into a thick turbulent boundary layer at Mach 6 are presented. Film cooling effectiveness, skin friction, and flow structure downstream of the swept slot injection were.
Influence of tangential injection on heat transfer to a cone in the transition reynolds number domain. Investigation of the three-dimensional turbulent flow downstream of swept slot injection in hypersonic flow. Investigation of the three-dimensional turbulent flow downstream of swept slot injection in hypersonic flow.
Film-Cooling Effectiveness and Skin Friction in Hypersonic Turbulent Flow. Influence of injectant Mach number and temperature on supersonic film cooling.
Investigation of the three-dimensional turbulent flow downstream of swept slot injection in hypersonic flow. Downstream influence of swept slot injection in hypersonic turbulent flow of tangential swept slot injection into a thick turbulent boundary layer at Mach 6 are presented.
flow structure. Film Cooling Effectiveness in Hypersonic Turbulent Flow,” Predicted Effects of Tangential Slot Injection on Turbulent Boundary Layer Flow Over a Wide Speed Range,” An Experimental Study on the Influence of Vortex Generators on the Shock-Induced Boundary Layer Separation at M = Abstract.
Large-eddy simulations are performed to analyze film cooling in supersonic combustion ramjets (Scramjets). The transonic film cooling flow is injected through a slot parallel to a Ma= main stream with a fully turbulent boundary injection Mach number is Ma i = and adiabatic wall conditions are imposed.
The cooling effectiveness is investigated for adverse and. Several classes of injection are considered including transverse jets, wall slots, and some hybrid cases.
The review is made difficult by the sparseness of the current database. Mixing data is summarized primarily in the form of the downstream decay of the maximum concentration. With the advancement of the air-breathing propulsion system, the supersonic vehicle technique has drawn a significant interest worldwide.
The mixing a. Correlations have been made in NASA Langley's Mach Pilot Quiet Tunnel for the transitions occurring from laminar to turbulent flow, in the cases of deg and deg swept cylinders.
Hypersonic transition from fully laminar to fully developed turbulent flow occurs over a finite spatial extent. The arclength from onset to completion can equal the arclength from the nose to onset, so this finite extent can be substantial.
However, much of the extant literature reduces the raw data to an analysis of the transition ‘point’. A computational-based investigation has been carried out to examine the heat transfer effects of normal and tangential blowing on blunt surfaces exposed to high Mach number flows.
Experimental results from such studies where a controlled outflow is imposed upon a surface under hypersonic conditions are few and far between. Simple 3D axisymmetric configurations supporting flat front surfaces.
() Flow Behind a Step in High-Enthalpy Laminar Hypersonic Flow. AIAA Journal() Investigation of Heat-Flux in High Enthalpy Hypersonic Flow Over a. the transition to turbulent structures in the turbulent boundary layer.
Figure 2b) shows the RMS-Values of the downstream arranged piezo sensors for diﬀerent velocities. Since the maximum of the signal amplitudes indicates the transition, the RMS-curves show the location of transition on the glove. This article is divided into two parts.
The first part focuses on the incompressible boundary layer. The general background of different flow structures and the limitation of visualization techniques are reviewed first (Sec. II), and the structures of incompressible flow are described in detail (Sec.
III), including experimental and numerical visualization of structures, the similarity between. The extent and definition of the secondary flow-affected region on the suction surface are clearly evident at lower Reynolds numbers and lower turbulence levels when the suction surface flow is largely laminar.
The heat transfer in the plateau region has a magnitude similar to a turbulent boundary layer. Dependence of Turbulent Spot Initiation Rates on Hypersonic Boundary Layer Flow Parameters. Raghunath, Sreekanth, Narasimha, Roddam and Mee, David J.
Dependence of Turbulent Spot Initiation Rates on Hypersonic Boundary Layer Flow Parameters. 55th AIAA Aerospace Sciences Meeting and Exhibit, Dallas, TX, United States, January. The effects of localized injection through a porous strip on a turbulent boundary layer at zero pressure gradient conditions were examined experimentally.
The magnitude of the injection velocity was kept very small (less than 1% of the free-stream velocity) to prevent separation near the injection strip and to keep the perturbations small. It was found that the injection increases all the.Downstream influence of swept slot injection in hypersonic turbulent flow / (Washington: National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, ), by Jerry N.
Hefner, Dennis M. Bushnell, Aubrey M. Carey, Langley Research Center, and United States National Aeronautics and.USA1 US15/, USA USA1 US A1 US A1 US A1 US A US A US A US A1 US A1 US A1 Authority US United States Prior art keywords flow means shock cvg wing Prior art date Legal status (The legal status is an assumption .