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  • AERODYNAMICS  (6)
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  • 1
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    Application of Navier-Stokes code PAB3D with kappa-epsilon turbulence model to attached and separated flows (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A three-dimensional Navier-Stokes solver was used to determine how accurately computations can predict local and average skin friction coefficients for attached and separated flows for simple experimental geometries. Algebraic and transport equation closures were used to model turbulence. To simulate anisotropic turbulence, the standard two-equation turbulence model was modified by adding nonlinear terms. The effects of both grid density and the turbulence model on the computed flow fields were also investigated and compared with available experimental data for subsonic and supersonic free-stream conditions.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3480 , L-17354 , NAS 1.60:3480
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Study of supersonic intersection flowfield at modified wing-body junctions (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The problem of supersonic flow control using fillets and sweep for a wing-body junction has been investigated numerically using a three-dimensional Navier-Stokes code, which employs the MacCormack's time-split finite volume technique. An elliptic grid generation technique with direct control over spacing has been developed for constructing the grid at a filleted wing-body junction. The computed results for pressure distribution, particle paths, and limiting streamlines on the flat plate and fin surface for a swept fin show a decrease in the peak pressure on the fin leading edge and in the extent of the separated flow region. Moreover, the results for filleted juncture clearly show that the flow streamline patterns lose much of their vortical character with proper filleting. It has been demonstrated that fillets with a radius of three-and-one-half times the fin leading-edge diameter are required to weaken the vorticity in the horseshoe vortex by a factor of three for the Mach number and Reynolds number considered in the present study.
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 5; p. 877-883.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of three-dimensional separation at wing/body junctions in supersonic flows using TVD MacCormack's scheme (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A Total Variation Diminishing (TVD) MacCormack scheme is used to study the three-dimensional separation at wing/body junctions in supersonic flows. The new scheme is robust, resolves discontinuities well with-out any numerical oscillations present in the flow field. Moreover, this new scheme does not contain any problem dependent parameters to be adjusted and many production codes employing MacCormack algorithm can be easily updated to good effect. Numerical simulation carried out in laminar supersonic junction flows using the new scheme yields improved prediction for the separation location and the axial velocity profiles in the separated flow region.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0884 , AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States|; 11 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Control of supersonic intersection flowfields through filleting and sweep (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The problem of supersonic flow control using fillets and sweep for a wing/body junction has been investigated numerically using a three-dimensional Navier-Stokes code which employs the MacCormack time-split finite-volume technique. An elliptic grid generation technique with direct control over spacing has been incorporated for constructing the grid at a filleted wing/body junction. The computed results for pressure distribution, particle paths, and limiting streamlines on the flat plate and fin surface for a swept fin show a decrease in the peak pressure on the fin leading edge and in the extent of the separated flow region. Moreover, the results for the filleted juncture clearly show that the flow streamline patterns lose much of their vortical character with proper filleting. It is demonstrated that fillets with a radius of 3.5 times the fin leading edge diameter are required to weaken the usual necklace vortex interaction.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-3534 , AIAA, ASME, SIAM, and APS, National Fluid Dynamics Congress; Jul 25, 1988 - Jul 28, 1988; Cincinnati, OH; United States
    Format: text
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  • 5
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    Performance of a three-dimensional Navier-Stokes code on CYBER 205 for high-speed juncture flows (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A vectorized 3D Navier-Stokes code has been implemented on CYBER 205 for solving the supersonic laminar flow over a swept fin/flat plate junction. The code extends MacCormack's predictor-corrector finite volume scheme to a generalized coordinate system in a locally one dimensional time split fashion. A systematic parametric study is conducted to examine the effect of fin sweep on the computed flow field. Calculated results for the pressure distribution on the flat plate and fin leading edge are compared with the experimental measurements of a right angle blunt fin/flat plate junction. The decrease in the extent of the separated flow region and peak pressure on the fin leading edge, and weakening of the two reversed supersonic zones with increase in fin sweep have been clearly observed in the numerical simulation.
    Keywords: AERODYNAMICS
    Type: Applications of parallel processing in fluid mechanics; Jun 14, 1987 - Jun 17, 1987; Cincinnati, OH; United States
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    NASA TECHNICAL REPORTS
  • 6
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    A parametric study of three-dimensional separation at a wing/body junction for supersonic free-stream conditions (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The problem of three-dimensional separation at a wing/body junction has been investigated numerically using a three-dimensional Navier-Stokes code which employs the MacCormack's time split finite volume technique. An algebraic grid generation technique is used for generating the grid at a wing/body junction. Specific computational results on velocity and pressure distribution in the separated flow region are compared with the experimental results. A parametric study of flow parameters such as Mach number and Reynolds number have been carried out to understand their effect in interaction flow field. The parametric study indicates a strong dependency of the number of vortices at the junction on Mach number and Reynolds number.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-2198 , AIAA Applied Aerodynamics Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, WA; United States
    Format: text
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