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Author: James L. Jacocks Publisher: ISBN: Category : Airplanes Languages : en Pages : 36
Book Description
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).
Author: James L. Jacocks Publisher: ISBN: Category : Airplanes Languages : en Pages : 36
Book Description
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).
Author: J. L. Jacocks Publisher: ISBN: Category : Languages : en Pages : 31
Book Description
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).
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
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).
Author: Gary D. Kuhn Publisher: ISBN: Category : Languages : en Pages : 94
Book Description
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: 9781722971144 Category : Languages : en Pages : 122
Book Description
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...
Author: John A. Benek Publisher: ISBN: Category : Languages : en Pages : 216
Book Description
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).
Author: James L. Jacocks
Author: James L. Jacocks
Author: J. L. Jacocks
Author: 
Author: John A. Benek
Author: Frederick C. Guyton
Author: Gary D. Kuhn
Author: National Aeronautics and Space Administration (NASA)
Author: John A. Benek
Author: 
Author: