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  • AERODYNAMICS  (386)
  • Fluid Mechanics and Heat Transfer
  • 1990-1994  (375)
  • 1955-1959  (26)
  • 1
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    An embedded grid formulation applied to a delta wing (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Applications using a three-dimensional embedded grid scheme are made to high angle of attack viscous flow over two bodies: a slender cone using the conical approximation and a 75 deg swept delta wing. The embedded grids are used principally to improve the numerical resolution of the separated vortical flow above the body. Detailed comparisons are made with experimental measurements of the velocity field over the delta wing. The prediction of the maximum steamwise velocity is improved using two levels of embedded grid refinement but is still less than the experimental measurements available from a laser velocimeter.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0429
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Computational fluid dynamics for hypersonic airbreathing aircraft (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A development status evaluation is presented for CFD methods applicable to fuselage-integrated scramjet powerplant incorporating hypersonic vehicles; these methods are critically important due to the unavailability of experimental facilities for such elevated Mach number/high-enthalphy conditions. Advancements are required in algorithm robustness and speed, geometric flexibility, and the inclusion of more complete flow physics. The most serious deficiencies lie in turbulence modeling, the lack of complete transition-prediction methods, and combustion modeling.
    Keywords: AERODYNAMICS
    Type: In: Hypersonic flows for reentry problems. Vol. 1 (A93-42576 17-02); p. 55-71.
    Format: text
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  • 3
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    Computational study of incipient leading-edge separation on a supersonic delta wing (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 203-209
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    NASA TECHNICAL REPORTS
  • 4
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    Strake camber and thickness design procedure for low alpha supersonic flow (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 27; 481-487
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  • 5
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    Euler analysis of a High-Speed Civil Transport concept at Mach 3 (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 28; 239-245
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  • 6
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    Unsteady flow past an airfoil pitched at constant rate (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The unsteady flow past a NACA 0012 airfoil that is undertaking a constant-rate pitching up motion is investigated experimentally by the PIDV technique in a water towing tank. The Reynolds number is 5000, based upon the airfoil's chord and the free-stream velocity. The airfoil is pitching impulsively from 0 to 30 deg. with a dimensionless pitch rate alpha of 0.131. Instantaneous velocity and associated vorticity data have been acquired over the entire flow field. The primary vortex dominates the flow behavior after it separates from the leading edge of the airfoil. Complete stall emerges after this vortex detaches from the airfoil and triggers the shedding of a counter-rotating vortex near the trailing edge. A parallel computational study using the discrete vortex, random walk approximation has also been conducted. In general, the computational results agree very well with the experiment.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Research Center, Physics of Forced Unsteady Separation; p 35-59
    Format: application/pdf
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  • 7
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    Integration of a mechanical forebody vortex control system into the F-15 (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The goal of the F-15 Forebody Vortex Control (FVC) program is to develop a production FVC system for the F-15. The system may consist of either a mechanically actuated device such as the strakes developed for the HARV program, or a pneumatic device such as the port blowing system being tested on the X-29. Both types of systems are being evaluated under this program. Background information on the F-15 and a description and overview of forebody vortex controls (FVC) will be presented.
    Keywords: AERODYNAMICS
    Type: NASA. Dryden Flight Research Center, Fourth High Alpha Conference, Volume 3; 20 p
    Format: application/pdf
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  • 8
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    Application of an efficient hybrid scheme for aeroelastic analysis of advanced propellers (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An efficient 3-D hybrid scheme is applied for solving Euler equations to analyze advanced propellers. The scheme treats the spanwise direction semi-explicitly and the other two directions implicitly, without affecting the accuracy, as compared to a fully implicit scheme. This leads to a reduction in computer time and memory requirement. The calculated power coefficients for two advanced propellers, SR3 and SR7L, and various advanced ratios showed good correlation with experiment. Spanwise distribution of elemental power coefficient and steady pressure coefficient differences also showed good agreement with experiment. A study of the effect of structural flexibility on the performance of the advanced propellers showed that structural deformation due to centrifugal and aero loading should be included for better correlation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0028
    Format: text
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  • 9
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    A grid-independent approximate Riemann solver with applications to the Euler and Navier-Stokes equations (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new two-dimensional approximate Riemann solver has been developed that obtains fluxes on grid faces via wave decomposition. By utilizing information propagation in the velocity-difference directions rather than in the grid-normal directions, this flux function more appropriately interprets and hence more sharply resolves shock and shear waves when they lie oblique to the grid. The model uses five waves to describe the difference in states at a grid face. Two acoustic waves, one shear wave, and one entropy wave propagate in the direction defined by the local velocity difference vector, while the fifth wave is a shear wave that propagates at a right angle to the other four. Test cases presented include a shock reflecting off a wall, a pure shear wave, supersonic flow over an airfoil, and viscous separated airfoil flow. Results using the new model give significantly sharper shock and shear contours than a grid-aligned solver. Navier-Stokes computations over an aifoil show reduced pressure distortions in the separated region as a result of the grid-independent upwinding.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0239
    Format: text
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  • 10
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    Navier-Stokes solutions about the F/A-18 wing-LEX-fuselage configuration with multi-block structured grids (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Three-dimensional thin-layer Navier-Stokes computations are presented for the F/A-18 configuration. The modeled configuration includes an accurate surface representation of the fuselage, leading-edge-extension, as well as the wing with and without leading-edge-flap deflection. A multi-block structured volume grid with various topologies is generated using transfinite interpolation technique. The flowfield domain is divided into twenty blocks, each representing a particular geometrical complexity of the configuration. The results are obtained from an algorithm for solving the compressible Navier-Stokes equations that incorporates an upwind-biased, flux-difference-splitting approach. In addition, a newly developed capability that allows for generalized surface patching among blocks is employed. Turbulent results are presented for flow conditions that correspond to recent NASA F/A-18 High Alpha Research Vehicle flight experiments. Good correlations between the computations and the flight test results are disclosed for both surface flow patterns as well as surface pressure distributions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3291 , AIAA Applied Aerodynamics Conference; Sept. 23-25, 1991; Baltimore, MD; United States
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