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There are a total of 55 record(s) matching your query.
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Application of shock capturing and characteristics methods to shuttle flow fields
Author(s): Kutler, P.; Rakich, J. V.; Mateer, G. G.
Abstract: The calculation of real gas flows around the space shuttle vehicle can be accomplished by the method of characteristics (MOC) or shock capture technique (SCT). Results obtained with these methods for an early orbiter shape ...
NASA Center: Ames Research Center
Publication Year: 1972
Added to NTRS: 2008-11-10
Accession Number: 72N20850; Document ID: 19720013200
Three-dimensional, shock-on-shock interaction problem
Author(s): Kutler, P.; Sakell, L.
Abstract: The unsteady, three-dimensional flow field resulting from the interaction of a plane shock with a cone-shaped vehicle traveling supersonically was determined using a second-order, shock-capturing, finite-difference approach. ...
NASA Center: Ames Research Center
Publication Year: 1975
Added to NTRS: 2008-11-10
Accession Number: 76N10048; Document ID: 19760002960; Report Number: PAPER-75-46
Internal and external axial corner flows
Author(s): Kutler, P.; Shankar, V.; Anderson, D. A.; Sorenson, R. L.
Abstract: The inviscid, internal, and external axial corner flows generated by two intersecting wedges traveling supersonically are obtained by use of a second-order shock-capturing, finite-difference approach. The governing equations ...
NASA Center: Ames Research Center
Publication Year: 1975
Added to NTRS: 2008-11-10
Accession Number: 76N10029; Document ID: 19760002941
Computation of the inviscid supersonic flow about cones at large angles of attack by a floating discontinuity approach
Author(s): Daywitt, J.; Kutler, P.; Anderson, D.
Abstract: The technique of floating shock fitting is adapted to the computation of the inviscid flowfield about circular cones in a supersonic free stream at angles of attack that exceed the cone half-angle. The resulting equations ...
NASA Center: Ames Research Center
Publication Year: 1977
Added to NTRS: 2008-06-30
Accession Number: 77N31095; Document ID: 19770024151; Report Number: A-7104, NASA-TM-73259
Diffraction of a shock wave by a compression corner; regular and single Mach reflection
Author(s): Vijayashankar, V. S.; Kutler, P.; Anderson, D.
Abstract: The two dimensional, time dependent Euler equations which govern the flow field resulting from the injection of a planar shock with a compression corner are solved with initial conditions that result in either regular ...
NASA Center: Ames Research Center
Publication Year: 1976
Added to NTRS: 2008-06-30
Accession Number: 77N18387; Document ID: 19770011443; Report Number: A-6804, NASA-TM-X-73178
Numerical study of unsteady viscous hypersonic blunt body flows with an impinging shock
Author(s): Klopfer, G. H.; Yee, H. C.; Kutler, P.
Abstract: A complex two-dimensional, unsteady, viscous hypersonic shock wave interaction is numerically simulated by a high-resolution, second-order fully implicit shock-capturing scheme. The physical model consists of a nonstationary ...
NASA Center: Ames Research Center
Publication Year: 1988
Added to NTRS: 2005-10-13
Accession Number: 88N22650; Document ID: 19880013266; Report Number: A-88147, NAS 1.15:100096, NASA-TM-100096
Application of second-order-accurate Total Variation Diminishing (TVD) schemes to the Euler equations in general geometries
Author(s): Yee, H. C.; Kutler, P.
Abstract: A one-parameter family of explicit and implicit second-order-accurate, entropy satisfying, total variation diminishing (TVD) schemes was developed by Harten. These TVD schemes were the property of not generating spurious ...
NASA Center: Ames Research Center
Publication Year: 1983
Added to NTRS: 2005-10-13
Accession Number: 83N35710; Document ID: 19830027439; Report Number: A-9501, NAS 1.15:85845, NASA-TM-85845
Simulated Hypersonic Flows About A Blunt Body
Author(s): Kutler, P.; Yee, H. C.; Klopfer, G. H.
Abstract: Unsteady and steady flows compared. Report describes computer numerical study of two-dimensional, unsteady, viscous, hypersonic flows of air about blunt body with impinging shock. This kind of flow represents many practical ...
NASA Center: Ames Research Center
Publication Year: 1990
Added to NTRS: 2005-09-30
Accession Number: 90B10361; Document ID: 19900000361; Report Number: ARC-12251
Prediction of high speed propeller flow fields using a three-dimensional Euler analysis
Author(s): Bober, L. J.; Chaussee, D. S.; Kutler, P.
Abstract: To overcome the limitations of classical propeller theory, a computer program, NASPROP-E, was developed which solves for the flow field surrounding a multibladed propeller and axisymmetric nacelle combination using a finite ...
NASA Center: Ames Research Center, Glenn Research Center
Publication Year: 1983
Added to NTRS: 2004-11-03
Accession Number: 83N19710; Document ID: 19830011439; Report Number: AIAA PAPER 83-0188, E-1563, NAS 1.15:83065, NASA-TM-83065
Numerical study of unsteady viscous hypersonic blunt body flows with an impinging shock
Author(s): Klopfer, G. H.; Yee, H. C.; Kutler, P.
Abstract: A complex two-dimensional, unsteady, viscous hypersonic shock wave interaction is numerically simulated by a high-resolution, second-order fully implicit shock-capturing scheme. The physical model consists of a nonstationary ...
NASA Center: Ames Research Center
Publication Year: 1989
Added to NTRS: 2004-11-03
Accession Number: 89A45394; Document ID: 19890058023
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