4 edition of Computation of separation ahead of blunt fin in supersonic turbulent flow found in the catalog.
Computation of separation ahead of blunt fin in supersonic turbulent flow
by National Aeronautics and Space Administration, Ames Research Center, For sale by the National Technical Information Service in Moffett Field, Calif, [Springfield, Va
Written in English
|Series||NASA technical memorandum -- 89416.|
|Contributions||Ames Research Center.|
|The Physical Object|
assuming the balance of a surface tension and a normal component of a viscous stress. Mori discussed the free surface flows before the wave breaking took divided the flow into three stages; the development of the free surface shear layer, the formation of the necklace vortex and the production of unsteady turbulent free surface flow. This implies weaker shockwaves and therefore weak shock turbulent interaction. At this point, we expect a more robust flow, but this will be investigated in some future project. Objective. The main objective of the project was to perform numerical simulations of a supersonic jet at high Reynolds number with turbulent inflow conditions.
are usually conducted in supersonic wind tunnels, using air as working fluid, and they are called the "cold" tests. The general influence of tab on supersonic flow in a divergent section of a 2D nozzle is schematically shown in Fig. 4. The protruding tab produces a recirculation zone (separated boundary layer domain) in front of it, which. 5 F. Computational conditions Inlet flow Mach number and Reynolds number based on height of backward-facing step and free stream velocity are and , respectively. 99 percent boundary layer thickness is h at x/h= Inflow boundary layer is turbulent is boundary layer.
Abstract: Turbulent transition is of great significance in modern sciences and industrial applications. The physics of flow instability and turbulent transition in shear flows is studied by analyzing the energy variation of fluid particles under the interaction of Cited by: pipe flow can be used to decrease the flow transfer costs. Ahsan perform CFD analysis for simulating fully turbulent flow in a pipe at higher Reynolds number. keε turbulence model has been adopted to solve the governing equation of fluid flow at high Reynolds number with enhanced wall : Prakash Chand.
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Get this from a library. Computation of separation ahead of blunt fin in supersonic turbulent flow. [Ching-Mao Hung; Ames Research Center.]. The effects of leading edge shape and angle of attack were studied.
Surface pressure measurements, and flow visualizations were made. The results show that, on the test surface near the fin, the structure of the vortex in the reverse flow region depends strongly on the leading edge shape, but it does not affect the flow near the separation by: 4.
SUPERSONIC, TURBULENT FLOW COMPUTATION AND DRAG OPTIMIZATION FOR AXISYMMETRIC AFTERBODIES. CUMMINGS,‘t H. YANG’ and Y. OH’ effects of separation, compression and/or expansion, and shock formation in the vicinity of the corner, (3) the structure of the recirculating zone, (4) the formation and structure of a mixing.
Select COMPUTATION of SEPARATION AHEAD of BLUNT FIN in SUPERSONIC TURBULENT FLOW. Book chapter Full text access. COMPUTATION of SEPARATION AHEAD of BLUNT FIN in SUPERSONIC TURBULENT FLOW.
Ching-mao Hung. Frontiers of Fluid Mechanics documents the proceedings of the Beijing International Conference on Fluid Mechanics, held. On the Connection Between Near and Far Pressure Fields of a Turbulent Jet Computation of separation ahead of blunt fin in supersonic turbulent flow Separation ahead of a Author: Dimitri Papamoschou.
Computation of separation ahead of blunt fin in supersonic turbulent flow [microform]  Hung, Ching-mao. Moffett Field, Calif.: National Aeronautics and Space Administration, Ames Research Center ; [Springfield, Va. JOURNAL OF COMPUTATIONAL PHYS () Computation of Turbulent Supersonic Flows around Pointed Bodies Having Crossflow Separation DAVID DEGANI* AND LEWIS B.
SCHIFF1^ NASA Ames Research Center, Moffett Field, California Received September 7, ; revised Janu A recently reported thin-layer parabolized Cited by: INVESTIGATION OF TURBm SEE'ARATE3) FLOWS IN TRE VICINITY OF FIN-TYPE PROTUBERANCES AT SUPERSONIC MACH NITMBERs* By Earl A.
Price, Jr., and Robert L. Stallings, Jr. Langley Research Center SUMMARY An experimental investigation has been conducted on the separated and asso ciated disturbed flow region resulting from the presence. 2. Bogdanoff and K. Kepler, “Separation of turbulent boundary layer in a supersonic flow,” Voprosy raketnoi tekhniki, no.
6, Cited by: 3. The blunt fin shock wave with strength depending on the sweep angle of the fin interacts with the boundary layer on the plate and creates a separated region with a complex flow structure.
The computation of turbulent flows has been a probiern of major concern sjnce the time of Osborne Reynolds. Until the rtdvcnt of the high-speed computers, the range of turbulent-flow problems that could be hand!ed was very limited. The advances during this period were msde prinliirily in the laboratory, whcre basic ifisights intoFile Size: 1MB.
flow transition data in section 5. The results are summarized in section 6. LAMINAR-TURBULENT TRANSITION CORRELATION IN SUPERSONIC/HYPERSONIC FLOW - ATTACHED VERSUS SEPARATED FLOW George A. Simeonides Hellenic Aerospace Industry, Tanagra, Schimatari, Greece Keywords: transition, supersonic, hypersonic, flat plate, cone, bluntness, separation.
buy numerical simulation of turbulent shock-induced separated flows: application to the supersonic over-expanded nozzle flow on free shipping on qualified orders. Supersonic Flow Control of Swept Shock Wave/Turbulent Boundary Layer Interaction Using Plasma Actuators.
Akshay S Deshpande, Purdue University. Abstract. The effect of plasma actuators on the physics of the swept shock-wave/boundary-layer interaction induced by a sharp fin is investigated in this study by means of Reynolds-averaged Navier-Stokes calculations, Author: Akshay Shrikant Deshpande, Jonathan Poggie.
Computation of turbulent flows using an extended k-epsilon turbulence closure model Item Preview remove-circle Share or Embed This Item.
turbulent boundary layer flow, turbulent flow over a backward-facing step, and a confined turbulent swirling flow. A second-order accurate finite difference boundary layer code and a nearly second-order.
tions with the space separation in the direction of the mean flow are characterized by a convection speed Uc, and this speed falls from of the free-steam velocity arm = to arm = 5. The peak value of the correla--tion coefficient falls to one-half for a spacial separation of the measuring points of about two-tenths of the boundary.
The steady two-dimensional viscous supersonic turbulent flow over a backward facing step was calculated using the PHOENICS CFD code. The two-equation k– turbulence model was employed for the turbulent flow simulation. The effects of the incoming boundary layer, Reynolds number and inlet Mach number on the flow were investigated.
Supersonic Turbulent Flow Reattachment Downstream of a Two-Dimensional Backstep, AIAA Paper No. C.; Page, R. Reda] on *FREE* shipping on Author: Reda, D. C.; Page, R. Analysis of Buzz in a Supersonic Inlet NASA/TM— May NASA STI Program in Proﬁ le although the book predates most of the computational studies described below.
Buzz was first was used to visualize the flow ahead of the inlet. A high-speed Phantom V camera operating at Full text of "Computation of turbulent flows using an extended k-epsilon turbulence closure model" See other formats NASA CONTRACTOR REPORT NASA CR COMPUTATION OF TURBULENT FLOWS USING AN EXTENDED k-£ TURBULENCE CLOSURE MODEL By Y.-S.
Chen and S.-W. Kim Universities Space Research Association Structures and Dynamics. Computational Fluid Dynamics Validation of Supersonic Parachute Analysis Because the flow field is highly turbulent and unsteady, the numerical method uses Detached Eddy Simulation (DES). This is a good choice because the capsule has a .The bypass duct can also be used to divert separated flow from the sharp lip away from the core flow.
Separation is a common problem with sharp-lipped supersonic inlets at low subsonic speeds and at angles of attack or yaw. In Ref. 5 it was shown that lip separation at low takeoff speeds could be contained in the bypass duct by blocking the. Report presents the results of experimental and theoretical research conducted on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation.
Results were obtained from pressure-distribution measurements, shadowgraph observations, high-speed Cited by: