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  • 1980-1984  (12)
  • 1
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    Supersonic axisymmetric flow over boattails containing a centered propulsive jet (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 22; 1358-136
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Topological analysis of computed three-dimensional viscous flow fields (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Computed solutions of the time-dependent, Reynolds-averaged Navier-Stokes equations for three-dimensional flows having thin shear layers are analyzed, using topological concepts. Specific examples include the transonic flow over a body of revolution with conical afterbody at moderate angles of incidence to the free stream. Experimental flow-visualization techniques are simulated graphically to visualize the computed flow. Scalar and vector fluid dynamic properties, such as pressure, shear stress, and vorticity on the body surface, are presented as topological maps, and their relationship to one another in terms of orientation and singular points is discussed. The extrapolation from these surface topologies toward the understanding of external flow-field behavior is discussed and demonstrated.
    Keywords: AERODYNAMICS
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    NASA TECHNICAL REPORTS
  • 3
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    Finite difference simulation of unsteady interactive flows (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The development of time-dependent numerical simulations of unsteady interactive flows of an aerodynamic nature is reviewed with emphasis on compressible flows at flight Reynolds numbers and noniterative schemes based on Navier-Stokes equations. The importance of writing the equations in strong conservation-law form for a generalized body-oriented coordinate system is pointed out. The discussion covers time and length scales and numerical methods currently in use. Some computed results are presented and compared with experimental data.
    Keywords: AERODYNAMICS
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    NASA TECHNICAL REPORTS
  • 4
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    Time-dependent finite-difference simulation of unsteady interactive flows (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The solution of the time-dependent, Reynolds-averaged, Navier-Stokes equations for unsteady, interacting flows by finite-difference algorithms is discussed. Specific examples include (1) unsteady transonic flow over a thick biconvex airfoil, (2) determination of buffet boundaries for a transonic lifting airfoil, (3) the simulation of aileron buzz and (4) dynamic stall. Algorithms considered include explicit methods, mixed (or hybrid) methods, and fully implicit methods. Consideration of time scales for computational stability, computational accuracy, and physical accuracy and the use of time-dependent adaptive meshing to realize computational efficiency are also discussed.
    Keywords: AERODYNAMICS
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    NASA TECHNICAL REPORTS
  • 5
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    Three-dimensional flow over a conical afterbody containing a centered propulsive jet: A numerical simulation (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The supersonic flow field over a body of revolution incident to the free stream is simulated numerically on a large, array processor (the CDC CYBER 205). The configuration is composed of a cone-cylinder forebody followed by a conical afterbody from which emanates a centered, supersonic propulsive jet. The free-stream Mach number is 2, the jet-exist Mach number is 2.5, and the jet-to-free-stream static pressure ratio is 3. Both the external flow and the exhaust are ideal air at a common total temperature.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA. Goddard Space Flight Center CYBER 200 Appl. Seminar; p 185-197
    Format: application/pdf
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  • 6
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    A practical adaptive-grid method for complex fluid-flow problems (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A practical solution, adaptive-grid method utilizing a tension and torsion spring analogy is proposed for multidimensional fluid flow problems. The tension spring, which connects adjacent grid points to each other, controls grid spacings. The torsion spring, which is attached to each grid node, controls inclinations of coordinate lines and grid skewness. A marching procedure was used that results in a simple tridiagonal system of equations at each coordinate line to determine grid-point distribution. Multidirectional adaptation is achieved by successive applications of one-dimensional adaptation. Examples of applications for axisymmetric afterbody flow fields and two dimensional transonic airfoil flow fields are shown.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85989 , A-9803 , NAS 1.15:85989
    Format: application/pdf
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  • 7
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    Topological analysis of computed three-dimensional viscous flow fields (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Computed solutions of the time-dependent, Reynolds-averaged Navier-Stokes equations for three dimensional flows having thin shear layers are analyzed using topological concepts. Specific examples include the transonic flow over a body of revolution with conical afterbody at moderate angles of incidence to the free stream. Experimental flow-visualization techniques are simulated graphically to visualize the computed flow. Scalar and vector fluid dynamics properties such as pressure, shear stress, and vorticity on the body surface are presented as topological maps, and their relationship to one another in terms of orientation and singular points is discussed. The extrapolation from these surface topologies toward the understanding of external flow-field behavior is and demonstrated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-84255 , A-8968 , NAS 1.15:84255
    Format: application/pdf
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  • 8
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    Three-dimensional flow over a conical afterbody containing a centered propulsive jet - A numerical simulation (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The supersonic flow field over a body of revolution incident to the free stream is simulated numerically on a large, array processor (the CDC Cyber 205). The configuration is composed of a cone-cylinder forebody followed by a conical afterbody from which emanates a centered, supersonic propulsive jet. The free-stream Mach number is 2, the jet-exit Mach number is 2.5, and the jet-to-free-stream static pressure ratio is 3. Both the external flow and the exhaust are ideal air at a common total temperature. The thin-layer approximation to the time-dependent, compressible, Reynolds-averaged Navier-Stokes equations are solved using an implicit finite-difference algorithm. The data base, of 5 million words, is structured in a 'pencil' format so that efficient use of the array processor can be realized. The computer code is completely vectorized to take advantage of the data structure. Turbulence closure is achieved using an empirical algebraic eddy-viscosity model. The configuration and flow conditions correspond to published experimental tests and the computed solutions are consistent with the experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1709
    Format: text
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  • 9
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    Theoretical analysis of aircraft afterbody flow (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The strongly interactive flow field about aircraft afterbodies is investigated using computational techniques by which the thin-shear-layer formulation of the compressible, Reynolds-averaged Navier-Stokes equations is solved. A time-dependent implicit numerical algorithm is used to obtain solutions for a variety of afterbody and nozzle geometries, within the class of bodies of revolution, for both subsonic and supersonic external flow, and for sonic and supersonic underexpanded jets. Only centered nozzles with either a sharp lip or a blunt base are considered. In all cases, computed results are compared with experimental data taken at flight Reynolds numbers for like-flow conditions. Turbulence closure is realized using algebraic eddy-viscosity concepts. A new and unique adaptive-grid technique is used to resolve flow regimes with large gradients and to improve the accuracy and efficiency of the computational scheme. Special singular point boundary conditions are used for similar purposes, and are especially effective for highly under-expanded jets. For all cases considered, except one with a very large base-to-nozzle-exit-diameter ratio, the agreement with experimental measurements is excellent. For geometries with large base regions, enhancements in the turbulence transport model are necessary to support improvements in the flow-field simulation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1524
    Format: text
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  • 10
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    Numerical Simulation of Three-Dimensional Boattail Afterbody Flowfields (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The thin shear-layer approximations of the three-dimensional, compressible Navier-Stokes equations are solved for subsonic, transonic, and supersonic now over axisymmetric boattail bodies at moderate angles of attack. The plume is simulated by a solid body configuration identical to those used In experimental tests. An implicit algorithm of second-order accuracy is used to solve the equations on the ILLIAC 4 computer. The turbulence is expressed by an algebraic model applicable to three-dimensional flowfields with moderate separation. The formulation used is attractive in its independence of boundary-layer parameters. Such a simple model, however, is incapable of supporting detailed quantitative descriptions of complex shear flows. Never-the-less, good qualitative comparisons are found with three different sets of experimental date. Quantitative improvement will depend on improved turbulence transport descriptions.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA/TM-1981-207528 , NAS 1.15:207528 , AIAA Paper 80-1347R , Fluid and Plasma Dynamics Conference; Jul 14, 1980 - Jul 16, 1980; Snowmass, CO; United States|AIAA Journal; 19; 5; 582-588
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