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dc.contributor.authorAllmaras, Steven R. (Steven Richard)en_US
dc.contributor.otherMassachusetts Institute of Technology. Gas Turbine Laboratoryen_US
dc.date.accessioned2016-10-06T21:22:17Z
dc.date.available2016-10-06T21:22:17Z
dc.date.issued1989en_US
dc.identifier.urihttp://hdl.handle.net/1721.1/104736
dc.descriptionMarch 1989en_US
dc.descriptionOriginally issued as: Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1989en_US
dc.descriptionIncludes bibliographical references (pages 238-243)en_US
dc.description.abstractThis thesis presents a coupled Euler/Navier-Stokes algorithm for solving 2-D unsteady transonic flows. The flowfield is described by a Defect formulation, where separate Euler and Navier-Stokes algorithms are used on overlapping grids and are coupled through wall transpiration fluxes. The work is separated into three major contributions. The first contribution is a new algorithm for the solution of the 2-D unsteady Euler equations. The algorithm incorporates flux-splitting to capture shocks crisply and with minimal oscillations. To reduce numerical errors, grid independent second order accuracy is achieved for both steady and unsteady flows. This is done by a formulation in which both solution averages and gradients are stored for each cell. The scheme allows no decoupled modes; hence, no explicitly added artificial is necessary. The second contribution is a Thin-Shear-Layer Navier-Stokes algorithm for viscous regions.en_US
dc.description.abstractThe algorithm uses two-point differencing across the boundary layer, which is second order accurate for both inviscid and viscous terms on nonsmooth grids. Fluxsplitting is used for the streamwise discretization to capture shocks. The spatial discretization of this scheme also admits no decoupled modes and does not require added artificial dissipation. A semi-implicit time integration is employed, which allows a time step determined by the streamwise grid spacing only. The algorithm uses a dynamic coordinate rescaling to evolve the viscous grid to the changing boundary layer thickness. The final contribution of the work is a explicit relaxation procedure for coupling the Euler and Navier-Stokes algorithms together. The coupling is through boundary conditions-specified outer edge values for the viscous solution and wall transpiration fluxes for the Euler solution. Computational results are presented for a series of duct geometries.en_US
dc.description.abstractThe test cases are used to demonstrate the accuracy of the Euler algorithm, the Navier-Stokes algorithm, and the fully coupled algorithm. Results are compared with analytic theory, experimental results, and other computational methods.en_US
dc.description.sponsorshipSupported by a grant from Rolls-Royce, PLC and by an AFRAPT Traineeship in conjunction with Pratt & Whitney Engineering Division, Hartford, CTen_US
dc.description.sponsorshipFunded by the Air Force Office of Scientific Research. F49620-78-C-0084en_US
dc.format.extent273 pagesen_US
dc.publisherCambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1989]en_US
dc.relation.ispartofseriesGTL report #196en_US
dc.subject.lccTJ778.M41 G24 no.196en_US
dc.subject.lcshNavier-Stokes equationsen_US
dc.subject.lcshEuler productsen_US
dc.subject.lcshFluid dynamicsen_US
dc.titleA coupled Euler/Navier-Stokes algorithm for 2-D unsteady transonic shock/boundary-layer interactionen_US
dc.title.alternativeUnsteady transonic shock/boundary-layer interaction, A coupled Euler/Navier-Stokes algorithm for 2-Den_US
dc.typeTechnical Reporten_US
dc.identifier.oclc21503969en_US


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