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  • 1
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    Simulation of powered-lift flows (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The primary objective is to expose government, industry, and academic scientists to work underway at NASA-Ames towards the application of CFD to the powered lift area. One goal is to produce the technologies which will be required in the application of numerical techniques to, for example, the Supersonic STOVL program. The progress to date on the following specific projects is presented: Jet in ground effect with crossflow; Jet in a crossflow; Delta planform with multiple jets in ground effect; Integration of CFD with thermal and acoustic analyses; Improved flow visualization techniques for unsteady flows; YAV-8B Harrier simulation program; and E-7 simulation program.
    Keywords: AERODYNAMICS
    Type: NASA Computational Fluid Dynamics Conference. Volume 2: Sessions 7-12; p 275-290
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Numerical simulation of a powered-lift landing (1993)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The flow field about a delta wing equipped with thrust reverse jets in slow speed flight near the ground has been computed. Results include the prediction of the flow about the delta wing at four fixed heights above the ground, and simulated landing, in which the delta wing descends towards the ground. Comparison of computed and experimental lift coefficients indicates that the simulations can capture at least the qualitative trends in lift-loss encountered by thrust-vectoring aircraft operating in ground effect.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD, Computational and Experimental Assessment of Jets in Cross Flow; 10 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic optimization studies on advanced architecture computers (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The approach to carrying out multi-discipline aerospace design studies in the future, especially in massively parallel computing environments, comprises of choosing (1) suitable solvers to compute solutions to equations characterizing a discipline, and (2) efficient optimization methods. In addition, for aerodynamic optimization problems, (3) smart methodologies must be selected to modify the surface shape. In this research effort, a 'direct' optimization method is implemented on the Cray C-90 to improve aerodynamic design. It is coupled with an existing implicit Navier-Stokes solver, OVERFLOW, to compute flow solutions. The optimization method is chosen such that it can accomodate multi-discipline optimization in future computations. In the work , however, only single discipline aerodynamic optimization will be included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-198045 , NAS 1.26:198045 , OMI-02-93
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Numerical simulation of a powered-lift landing, tracking flow features using overset grids, and simulation of high lift devices on a fighter-lift-and-control wing (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Attached as appendices to this report are documents describing work performed on the simulation of a landing powered-lift delta wing, the tracking of flow features using overset grids, and the simulation of flaps on the Wright Patterson Lab's fighter-lift-and-control (FLAC) wing. Numerical simulation of a powered-lift landing includes the computation of flow about a delta wing at four fixed heights as well as a simulated landing, in which the delta wing descends toward the ground. Comparison of computed and experimental lift coefficients indicates that the simulations capture the qualitative trends in lift-loss encountered by thrust-vectoring aircraft operating in ground effect. Power spectra of temporal variations of pressure indicate computed vortex shedding frequencies close to the jet exit are in the experimentally observed frequency range; the power spectra of pressure also provide insights into the mechanisms of lift oscillations. Also, a method for using overset grids to track dynamic flow features is described and the method is validated by tracking a moving shock and vortices shed behind a circular cylinder. Finally, Chimera gridding strategies were used to develop pressure coefficient contours for the FLAC wing for a Mach no. of 0.18 and Reynolds no. of 2.5 million.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-194260 , NAS 1.26:194260 , MCAT-93-18
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Numerical simulation of a complete STOVL aircraft in ground effect (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The ability to accurately predict vehicle performance without resorting to full-scale tests will be critical to future powered-lift aircraft projects. This paper summarizes efforts to predict the flow field about a powered-lift aircraft, the YAV-8B Harrier, in low level jet-borne flight by solution of the Reynolds-averaged Navier-Stokes equations. Results are compared with infrared images of the NASA YAV-8B Harrier V/STOL Systems Research Aircraft (VSRA) under similar flight conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3293 , AIAA Applied Aerodynamics Conference; Sept. 23-25, 1991; Baltimore, MD; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Numerical simulation of a complete STOVL aifcraft in ground effect (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamic environment encountered by powered-lift aircraft operating in ground effect is unique among flight vehicles. It is characterized by low forward speed with embedded regions of high subsonic or supersonic jet flows. During ground effect operations, complex recirculating flows generated by the jets produce large changes in the aerodynamic loads on the flight vehicle. Analytic prediction and small-scale experimental methods have produced mixed results in this flight regime, with the result that costly full-scale powered tests are required to evaluate the performance of candidate designs. The ability to accurately predict vehicle performance without resorting to full-scale tests will be critical to future powered-lift aircraft projects. This paper summarizes efforts to predict the flow field about a powered-lift aircraft, the YAV-8B Harrier, in low level jet-borne flight by solution of the Reynolds-averaged Navier-Stokes equations. Results are compared to infrared images of the NASA YAV-8B Harrier V/STOL Systems Research Aircraft (VSRA) under similar flight conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-4880 , ; 12 p.|Dec 01, 1993 - Dec 03, 1993; Santa Clara, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Numerical simulation of powered-lift flows (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This article presents work performed at NASA's Ames Research Center involving the application of Computational Fluid Dynamics (CFD) to the prediction of flows encountered by powered-lift aircraft operating in ground effect. These flows are characterized by jet and jet-induced flows interacting with the ground and aerodynamic surfaces. Over the last five years, work has progressed from simulating the interaction of a single jet impacting on a ground plane, through the simulation of a delta planform with multiple jets in ground effect, to an ongoing effort to simulate the complete flow about a Harrier AV-8B in ground effect. Efforts have also been made to predict the thermal interaction between hot propulsive jets and a landing surface of arbitrary thermal properties. Progress to date in each of these areas will be outlined.
    Keywords: AERODYNAMICS
    Type: ; 15 p.|Aug 29, 1990 - Aug 31, 1990
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Overset grid applications on distributed memory MIMD computers (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Analysis of modern aerospace vehicles requires the computation of flowfields about complex three dimensional geometries composed of regions with varying spatial resolution requirements. Overset grid methods allow the use of proven structured grid flow solvers to address the twin issues of geometrical complexity and the resolution variation by decomposing the complex physical domain into a collection of overlapping subdomains. This flexibility is accompanied by the need for irregular intergrid boundary communication among the overlapping component grids. This study investigates a strategy for implementing such a static overset grid implicit flow solver on distributed memory, MIMD computers; i.e., the 128 node Intel iPSC/860 and the 208 node Intel Paragon. Performance data for two composite grid configurations characteristic of those encountered in present day aerodynamic analysis are also presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-196081 , NAS 1.26:196081 , OMI-02-93 , AIAA Aerospace Sciences Meeting and Exhibit; Jan 09, 1995 - Jan 12, 1995; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Tracking flow features using overset grids (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A method is proposed to use overset grid topology to track dynamic flow features. Features of interest such as moving shock waves and vortices are overset with relatively fine tracker grids. Solutions are computed on the various grids and information is exchanged at intergrid boundaries. A grid track-sensor variable such as pressure is used to track the position of the flow feature to be resolved. The tracker grid is moved to the position where the track-sensor variable has the desired value (generally a maximum or a minimum) and new interpolation coefficients are computed for information exchange across grid boundaries. Solutions are computed at the current location and time-step, and grid motion is brought into the solution via time metrics. The method is demonstrated by tracking a moving shock and vortices shed behind a circular cylinder. It is conjectured that the method would show significant benefits in resolving features such as wakes behind oscillating airfoils and trajectories of jets issuing from rotating nozzles as encountered during thrust-vectoring.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0197 , ; 9 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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  • 10
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    Numerical simulation of STOL operations using thrust-vectoring (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The flow field about a delta wing equipped with thrust reverser jets in slow speed flight near the ground has been computed. Results include the prediction of the flow about the delta wing at four fixed heights above the ground, and a simulated landing, in which the delta wing descends towards the ground. Comparison of computed and experimental lift coefficients indicates that the simulations can capture at least the qualitative trends in lift-loss encountered by thrust-vectoring aircraft operating in ground effect.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-4254 , AIAA, Aircraft Design Systems Meeting; Aug 24, 1992 - Aug 26, 1992; Hilton Head Island, SC; United States|; 10 p.
    Format: text
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    NASA TECHNICAL REPORTS
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