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  • 1
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    Riblet drag at flight conditions (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 570-575
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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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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  • 3
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    Detailed flowfield measurements over a 75 deg swept delta wing for code validation (1988)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Selected results from an experimental investigation documenting the flowfield over 75 deg swept delta wing at an angle-of-attack of 20.5 deg are presented. Results obtained in the investigation include surface flow visualization, off-body flow visualization, and detailed flowfield surveys for various Reynolds numbers. Flowfield surveys at Reynolds numbers of 0.5, 1.0 and 1.5 million were conducted with both a pitot pressure probe and a 5-hole pressure probe; and 3-component laser Doppler velocimeter surveys were conducted at a Reynolds number of 1.0 million. The pitot pressure surveys were obtained at 5 longitudinal stations, the 5-hole probe surveys were obtained at 3 longitudinal stations and the laser Doppler velocimeter surveys were obtained at one station. The accuracy of each instrumentation system is discussed, as well as, discrepancies in the calculation of vorticity using various algorithms.
    Keywords: AERODYNAMICS
    Type: AGARD, Validation of Computational Fluid Dynamics. Volume 2: Poster Papers; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Measurement of leading edge vortices from a delta wing using a three component laser velocimeter (1986)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: An investigation of the flow field above a 75-deg swept delta wing at a 20.5-deg angle of attack is described. The experiment was performed in the NASA Langley Basic Aerodynamic Research Tunnel (BART) using an orthogonal three-component laser velocimeter. Preliminary laser velocimeter results show velocity vectors in the cross flow plane at x/c = 0.5, revealing the formation of the primary and secondary vortices over the upper surface of the wing.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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  • 5
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    Detailed flow-field measurements over a 75 deg swept delta wing (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results from an experimental investigation documenting the flowfield over a 75 deg swept delta wing at an angle-of-attack of 20.5 deg are presented. Results obtained include surface flow visualization, off-body flow visualization, and detailed flowfield surveys for various Reynolds numbers. Flowfield surveys at Reynolds numbers of 0.5, 1.0, and 1.5 million based on the root chord were conducted with both a Pitot pressure probe and a 5-hole pressure probe; and 3-component laser velocimeter surveys were conducted at a Reynolds number of 1.0 million. The Pitot pressure surveys were obtained at 5 chordwise stations, the 5-hole probe surveys were obtained at 3 chordwise stations and the laser velocimeter surveys were obtained at one station. The results confirm the classical roll up of the flow into a pair of primary vortices over the delta wing. The velocity measurements indicate that Reynolds number has little effect on the global structure of the flowfield for the Reynolds number range investigated. Measurements of the non-dimensional axial velocity in the core of the vortex indicate a jet like flow with values greater than twice freestream. Comparisons between velocity measurements from the 5-hole pressure probe and the laser velocimeter indicate that the pressure probe does a reasonable job of measuring the flowfield quantities where the velocity gradients in the flowfield are low.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2997 , L-16718 , NAS 1.60:2997
    Format: application/pdf
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  • 6
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    Requirements for facilities and measurement techniques to support CFD development for hypersonic aircraft (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The design of a hypersonic aircraft poses unique challenges to the engineering community. Problems with duplicating flight conditions in ground based facilities have made performance predictions risky. Computational fluid dynamics (CFD) has been proposed as an additional means of providing design data. At the present time, CFD codes are being validated based on sparse experimental data and then used to predict performance at flight conditions with generally unknown levels of uncertainty. This paper will discuss the facility and measurement techniques that are required to support CFD development for the design of hypersonic aircraft. Illustrations are given of recent success in combining experimental and direct numerical simulation in CFD model development and validation for hypersonic perfect gas flows.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: ; 11 p.
    Format: text
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  • 7
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    LDV surveys over a fighter model at moderate to high angles of attack (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The vortex flowfield over an advanced twin-tailed fighter configuration has been studied in a low-speed wind tunnel at two angles of attack using LDV, along with laser light sheet and surface flow visualizations. At 15 deg angles of attack, the vortices generated by the wing leading edge extension (LEX) were found to be unburst over the model and to pass outboard of the vertical tail. At 25 deg angle of attack, the vortices were shown to burst in the vicinity of the wing-LEX intersection and to impact directly on the vertical tails.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 881448
    Format: text
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  • 8
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    Inflow velocity measurements made on a helicopter rotor using a two-component Laser Velocimeter (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted in the 14- by 22-Foot Subsonic Tunnel at NASA Langley Research Center to measure the inflow into a scale model helicopter rotor in forward flight. The measurements were made with a two component Laser Velocimeter (LV) one chord above the plane formed by the path of the rotor tips (tips path plane). A conditional sampling technique was employed to determine the position of the rotor at the time that each velocity measurement was made so that the azimuthal fluctuations in velocity could be determined. The results of these tests were compared with inflow velocities predicted by a current technology rotor wake analysis program.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 87-1321
    Format: text
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  • 9
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    Active Flow Control Activities at NASA Langley (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA Langley continues to aggressively investigate the potential advantages of active flow control over more traditional aerodynamic techniques. This paper provides an update to a previous paper and describes both the progress in the various research areas and the significant changes in the NASA research programs. The goals of the topics presented are focused on advancing the state of knowledge and understanding of controllable fundamental mechanisms in fluids as well as to address engineering challenges. An organizational view of current research activities at NASA Langley in active flow control as supported by several projects is presented. On-center research as well as NASA Langley funded contracts and grants are discussed at a relatively high level. The products of this research are to be demonstrated either in bench-top experiments, wind-tunnel investigations, or in flight as part of the fundamental NASA R&D program and then transferred to more applied research programs within NASA, DOD, and U.S. industry.
    Keywords: Research and Support Facilities (Air)
    Type: AIAA Paper 2004-2623 , 2nd AIAA Flow Control Conference; Jun 28, 2004 - Jul 01, 2004; Portland, OR; United States
    Format: application/pdf
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  • 10
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    Effect of non-Poisson samples on turbulence spectra from laser velocimetry (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Spectral analysis of laser velocimetry (LV) data plays an important role in characterizing a turbulent flow and in estimating the associated turbulence scales, which can be helpful in validating theoretical and numerical turbulence models. The determination of turbulence scales is critically dependent on the accuracy of the spectral estimates. Spectral estimations from 'individual realization' laser velocimetry data are typically based on the assumption of a Poisson sampling process. What this Note has demonstrated is that the sampling distribution must be considered before spectral estimates are used to infer turbulence scales.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 32; 12; p. 2480-2481
    Format: text
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