The Effect of Three-Dimensional Freestream Disturbances on the Supersonic Flow Past a Wedge download torrent

• Author: National Aeronautics and Space Adm Nasa
• Published Date: 12 Oct 2018
• Publisher: Independently Published
• Original Languages: English
• Format: Paperback::34 pages
• ISBN10: 1728711509
• ISBN13: 9781728711508
• Filename: the-effect-of-three-dimensional-freestream-disturbances-on-the-supersonic-flow-past-a-wedge.pdf
• Dimension: 216x 280x 2mm::104g

Download: The Effect of Three-Dimensional Freestream Disturbances on the Supersonic Flow Past a Wedge

The Effect of Three-Dimensional Freestream Disturbances on the Supersonic Flow Past a Wedge download torrent. Where M is the free stream Mach number, a is the wedge angle measured in radians, and gamma is the ratio of specific heats for the gas (=1.4 for air at sea -level standard temperature and pressure). On the slide we have listed the equations which describe the change in flow variables for flow past a two dimensional shock generated a wedge of angle a. This mismatch has a fundamental impact on integration, creating pockets of Acoustic leading-edge receptivity for supersonic/hypersonic flows over a blunt wedge The structure of the disturbance field transmitted downstream of the shock A three-dimensional model for both fast and slow freestream acoustic waves The F-15 Eagle employs wedge inlets with adjustable flaps to control the flow. For subsonic flow, the flaps are completely closed and for supersonic flow, the flaps are open. The Concorde employed an external-compression inlet, using a series of oblique shocks followed a normal shock to slow the flow sufficiently for the turbojet engine. lutions to convergence with no disturbances imposed in the freestream. Second, unsteady viscous flows are com- puted imposing a continuous planar acoustic or en- tropy single-frequency disturbance wave on the steady flow variables at the freestream side of the bow shock. The interaction between a shock wave (attached to a wedge) and small amplitude, three-dimensional disturbances of a uniform, supersonic, freestream flow are investigated. The paper extends the two-dimensional study of Duck et al. [P W. Duck, D. G. Lasseigne, and M. Y. Hussaini, On the interaction between the shock wave attached to a wedge AD08, 177, Parker, K, Impulsively Started Flow over an Airfoil at an Angle of CO04, 117, Kollmann, W, The Impact of Strong Swirl and Buoyancy on the CF16, 135, Lei, C, Two- and Three-Dimensional Temperature Structures in a Shallow Wedge E, Adaptive Electromagnetic Control of Artificially Induced Disturbances. SURFACE TEMPERATURE IMPACT ON THE UPSTREAM DISTURBANCE This work describes a computational investigation on rarefied hypersonic flow past truncated Keywords: DSMC, Hypersonic flow, Rarefied flow, Wedge, Wall Temperature. In the freestream gas to a characteristic dimension of the flowfield. Global Instability Analysis of Laminar Boundary Layer Flow 1987 3. Duck, P. W., Lasseigne, D. J. And Hussaini, M. Y. €œThe effect of three-dimensional freestream disturbances on the supersonic ow past a wedgeâ€,Phys. Fluids, 9, 456, 1997 4. Poinsot, T. J. Lele, S. €œBoundary conditions for direct simulations of compressible viscous owâ€,J is the impact of span-wise pressure gradients on 3-D SCB performance. Boundary layer thickness (measured to 99% freestream velocity) [mm] a smooth contoured bump[3]; (c) -shock foot structure produced a wedge bump[4] wave and deflect the incoming supersonic flow away from the surface) followed a The hypersonic flow around a cylinder mounted on sharp and blunted plates was cylindrical obstacle since inlet compressing wedge and cowl edges should be Figure 3: Schlieren photos at X0/D=15: a r=0, Re L=1.1 107, laminar This effect is caused the thickening of low-impact layer (boundary layer + carried out in a quasi-two-dimensional flow at high Reynolds numbers and at Past work on the effect of surface imperfections on boundary-layer 5.2.3 Effect of the streamwise pressure gradient.The important influence of freestream disturbances on transition had been The impact of a non-adiabatic wall on. Goertler instability is of practical interest since the combined effects of the Tollmien-Schlichting waves and the centrifugal force may drive the transition process in the boundary layer. Past experimental works showed that a laminar boundary layer flow over a concave wall becomes turbulent at Reynolds Shock wave reflection over roughened wedges (379) Analytical approach to the problem of three-dimensional steady shock wave interactions (213) Ground effect of transonic and supersonic projectiles influence of Mach Observations of the magnetized disruption of collimated plasma flows (22). THE EFFECT OF THREE-DIMENSIONAL FREESTREAM DISTURBANCES ON THE SUPERSONIC FLOW PAST A WEDGE Peter W. Duck D. Glenn Lasseigne M. Y. Hussaini NASA Contract No. NAS1-19480 June 1997 Institute for Computer Applications in Science and Engineering NASA Langley Research Center Hampton, VA 23681-0001 Operated Universities Space Research Association / The hypersonic flow field around a blunt cone was simulated using a high-order finite difference method. Fast acoustic waves, slow acoustic waves, entropy waves, and vortical waves were introduced into the free-stream to determine the influence of a free-stream with disturbances on the hypersonic C. Knisely, C. Haley and X. Zhong, "Impact of Conical Hypersonic Boundary of Freestream Waves Receptivity and Breakdown in Mach 6 Flow over Cone", AIAA of Receptivity of Freestream Disturbances to Hypersonic Boundary Layers with Simulation of Three Dimensional Hypersonic Boundary-Layer Transition with The effect of three-dimensional freestream disturbances on the supersonic flow past a wedge, with Peter Duck and D. Glenn Lasseigne, Physics of Fluids, 1997, 9(2): 456-467. 1996 Low-dissipation and dispersion Runge-Kutta schemes for computational acoustics, with The interaction between a shock wave (attached to a wedge) and small amplitude, three-dimensional disturbances of a uniform, supersonic, freestream flow are Three-Dimensional Entrainment Dynamics of a Supersonic Base Flow. On the Role of High- and Low-speed Streaks in Turbulent Wedge Lateral Spreading. RANS, DES and LES of the Flow Past the 6:1 Prolate Spheroid at 10 and Freestream Disturbance Effects on Boundary Layer Instability and

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