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Computation Of Axisymmetric Separated Nozzle Afterbody Flow
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Book Synopsis Computation of Axisymmetric Separated Nozzle-afterbody Flow by : James L. Jacocks
Download or read book Computation of Axisymmetric Separated Nozzle-afterbody Flow written by James L. Jacocks and published by . This book was released on 1980 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of a computer program for solving the compressible, axisymmetric, mass-averaged Navier-Stokes equations is described. The basic numerical algorithm is the MacCormack explicit predictor-corrector scheme. Turbulence modeling is accomplished using an algebraic, two-layer eddy viscosity model with a novel modification dependent on the streamwise gradient of vorticity. Comparisons of computed results with experimental data are presented for several nozzle-afterbody configurations with either or simulated plumes. (Author).
Book Synopsis Computation of Axisymmetric Separated Nozzle-Afterbody Flow by : J. L. Jacocks
Download or read book Computation of Axisymmetric Separated Nozzle-Afterbody Flow written by J. L. Jacocks and published by . This book was released on 1980 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of a computer program for solving the compressible, axisymmetric, mass-averaged Navier-Stokes equations is described. The basic numerical algorithm is the MacCormack explicit predictor-corrector scheme. Turbulence modeling is accomplished using an algebraic, two-layer eddy viscosity model with a novel modification dependent on the streamwise gradient of vorticity. Comparisons of computed results with experimental data are presented for several nozzle-afterbody configurations with either or simulated plumes. (Author).
Book Synopsis Computation of Axisymmetric Separated Nozzle-Afterbody Flow by :
Download or read book Computation of Axisymmetric Separated Nozzle-Afterbody Flow written by and published by . This book was released on 1980 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of a computer program for solving the compressible, axisymmetric, mass-averaged Navier-Stokes equations is described. The basic numerical algorithm is the MacCormack explicit predictor-corrector scheme. Turbulence modeling is accomplished using an algebraic, two-layer eddy viscosity model with a novel modification dependent on the streamwise gradient of vorticity. Comparisons of computed results with experimental data are presented for several nozzle-afterbody configurations with either or simulated plumes. (Author).
Book Synopsis Separated and Nonseparated Turbulent Flows about Axisymmetric Nozzle Afterbodies by : John A. Benek
Download or read book Separated and Nonseparated Turbulent Flows about Axisymmetric Nozzle Afterbodies written by John A. Benek and published by . This book was released on 1979 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Evaluation of Nozzle Afterbody Code by : Frederick C. Guyton
Download or read book An Evaluation of Nozzle Afterbody Code written by Frederick C. Guyton and published by . This book was released on 1986 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computer Program for Calculation of Separated Turbulent Flows on Axisymmetric Afterbodies by : Gary D. Kuhn
Download or read book Computer Program for Calculation of Separated Turbulent Flows on Axisymmetric Afterbodies written by Gary D. Kuhn and published by . This book was released on 1977 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer code for a turbulent boundary-layer, inviscid interaction method for axisymmetric configurations of the type used for isolated nozzle afterbody models is presented. The method is applicable to flows subsonic free streams, including slightly supercritical flows. The method consists of an integral boundary-layer method and a finite-difference inviscid-flow method which are coupled iteratively through the boundary-layer displacement thickness. Both attached and separated boundary layers can be calculated. An option is provided for calculating two-dimensional boundary layers. The procedure for separated flows is to specify the displacement thickness of the boundary layer and calculate the free-stream velocity distribution from both the boundary-layer equations and the inviscid-flow equations. The separation point location and the angle of the displacement surface are found by an iterative procedure. The equations programmed are presented along with detailed instructions for the preparation of input data, description of the program output and instructions for operation of the program on an IBM 370 computer. Sample cases are provided for a complete axisymmetric interaction calculation and for a two-dimensional boundary-layer calculation.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722971144 Total Pages :122 pages Book Rating :4.9/5 (711 download)
Book Synopsis Comparison of Turbulence Models for Nozzle-Afterbody Flows with Propulsive Jets by : National Aeronautics and Space Administration (NASA)
Download or read book Comparison of Turbulence Models for Nozzle-Afterbody Flows with Propulsive Jets written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical investigation was conducted to assess the accuracy of two turbulence models when computing non-axisymmetric nozzle-afterbody flows with propulsive jets. Navier-Stokes solutions were obtained for a Convergent-divergent non-axisymmetric nozzle-afterbody and its associated jet exhaust plume at free-stream Mach numbers of 0.600 and 0.938 at an angle of attack of 0 deg. The Reynolds number based on model length was approximately 20 x 10(exp 6). Turbulent dissipation was modeled by the algebraic Baldwin-Lomax turbulence model with the Degani-Schiff modification and by the standard Jones-Launder kappa-epsilon turbulence model. At flow conditions without strong shocks and with little or no separation, both turbulence models predicted the pressures on the surfaces of the nozzle very well. When strong shocks and massive separation existed, both turbulence models were unable to predict the flow accurately. Mixing of the jet exhaust plume and the external flow was underpredicted. The differences in drag coefficients for the two turbulence models illustrate that substantial development is still required for computing very complex flows before nozzle performance can be predicted accurately for all external flow conditions. Compton, William B., III Langley Research Center CONVERGENT-DIVERGENT NOZZLES; NAVIER-STOKES EQUATION; NOZZLE FLOW; TURBULENCE MODELS; K-EPSILON TURBULENCE MODEL; JET EXHAUST; FREE FLOW; EXHAUST GASES; COMPUTATIONAL FLUID DYNAMICS; AXISYMMETRIC FLOW; ANGLE OF ATTACK; AERODYNAMIC COEFFICIENTS; PLUMES; REYNOLDS NUMBER; TURBULENCE; MACH NUMBER; DISSIPATION; AFTERBODIES; AERODYNAMIC DRAG...
Book Synopsis Separated and Nonseparated Turbulent Flows about Axisymmetric Nozzle Afterbodies. Part II. Detailed Flow Measurements by : John A. Benek
Download or read book Separated and Nonseparated Turbulent Flows about Axisymmetric Nozzle Afterbodies. Part II. Detailed Flow Measurements written by John A. Benek and published by . This book was released on 1979 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of mean velocity, specific turbulent kinetic energy, and specific Reynolds shear were obtained at M to the base infinity = 0.64 and ReD = 288,600 in a symmetry plane of two axisymmetric, circular-arc, boattail geometries each of which had a solid plume simulator. The geometries were selected such that an attached- and a separated flow boundary layer would be obtained. Ancillary measurements, consisting of model surface and tunnel wall, axial, static pressure distributions, and velocity vectors near the tunnel wall provide a well-defined domain with which to validate numerical flow simulations. Tabulations of the data and coefficients of least-squares dubic spline fits to the data are presented. (Author).
Download or read book NASA Technical Paper written by and published by . This book was released on 1981 with total page 518 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Solutions of the Navier-Stokes Equations for Transonic Afterbody Flows by :
Download or read book Numerical Solutions of the Navier-Stokes Equations for Transonic Afterbody Flows written by and published by . This book was released on 1980 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Solutions of the Navier-Stokes Equations for Transonic Afterbody Flows by : R. Charles Swanson
Download or read book Numerical Solutions of the Navier-Stokes Equations for Transonic Afterbody Flows written by R. Charles Swanson and published by . This book was released on 1980 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computer Program for Calculation of Separated Turbulent Flows on Axisymmetric Afterbodies Including Exhaust Plume Effects by : Gary D. Kuhn
Download or read book Computer Program for Calculation of Separated Turbulent Flows on Axisymmetric Afterbodies Including Exhaust Plume Effects written by Gary D. Kuhn and published by . This book was released on 1979 with total page 132 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer code for a turbulent boundary-layer, inviscid interaction method for axisymmetric configurations of the type used for isolated nozzle afterbody models is presented. The method is applicable to flows with subsonic free streams, including slightly supercritical flows and to bodies with either high pressure exhaust plumes or solid plume simulators. The method consists of an integral boundary-layer and plume-entrainment method and a finite-difference inviscid-flow method which are coupled iteratively through the boundary-layer displacement thickness. Both attached and separated boundary layers can be calculated. An option is provided for calculating two-dimensional boundary layers. The procedure for separated flows is to specify the displacement thickness of the boundary layer and calculate the free-stream velocity distribution from both the boundary-layer equations and the inviscid-flow equations. The separation point location and the angle of the displacement surface are found by an iterative procedure.
Book Synopsis Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 by : John R. Carlson
Download or read book Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 written by John R. Carlson and published by . This book was released on 1994 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Improved Analytical Model of the Separation Region on Boattail Nozzles at Subsonic Speeds by : Walter M. Presz
Download or read book An Improved Analytical Model of the Separation Region on Boattail Nozzles at Subsonic Speeds written by Walter M. Presz and published by . This book was released on 1978 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book RAXJET written by Richard G. Wilmoth and published by . This book was released on 1982 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Validation of the NPARC Code for Nozzle Afterbody Flows at Transonic Speeds by : James R. DeBonis
Download or read book Validation of the NPARC Code for Nozzle Afterbody Flows at Transonic Speeds written by James R. DeBonis and published by . This book was released on 1995 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1989 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt:
