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  • 1
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    Wake flow in adverse pressure gradient (2002)
    Elsevier
    Details
    Publication Date: 2002-10-01
    Print ISSN: 0142-727X
    Electronic ISSN: 1879-2278
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    A supercritical airfoil experiment (1994)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The purpose of this investigation is to provide a comprehensive data base for the validation of numerical simulations. The initial results of the study (single angle of attack) were presented in ref. 1, where the effects of various parameters and the adequacies of selected turbulence models were discussed. The objective of the present paper is to provide a tabulation of the experimental data. The data were obtained in the two-dimensional, transonic flowfield surrounding a supercritical airfoil. A variety of flows were studied in which the boundary layer at the trailing edge of the model was either attached or separated. Unsteady flows were avoided by controlling the Mach number and angle of attack. Surface pressures were measured on both the model and wind tunnel walls, and the flowfield surrounding the model was documented using a laser Doppler velocimeter (LDV). Although wall interference could not be completely eliminated, its effect was minimized by employing the following techniques. Sidewall boundary layers were reduced by aspiration, and upper and lower walls were contoured to accommodate the flow around the model and the boundary-layer growth on the tunnel walls. A data base with minimal interference from a tunnel with solid walls provides an ideal basis for evaluating the development of codes for the transonic speed range because the codes can include the wall boundary conditions more precisely than interference corrections can be made to the data sets.
    Keywords: AERODYNAMICS
    Type: AGARD, A Selection of Experimental Test Cases for the Validation of CFD Codes, Volume 2; 12 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Boundary-layer transition and global skin friction measurement with an oil-fringe imaging technique (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new oil-fringe imaging system skin friction (FISF) technique to measure skin friction on wind tunnel models is presented. In the method used to demonstrate the technique, lines of oil are applied on surfaces that connect the intended sets of measurement points, and then a wind tunnel is run so that the oil thins and forms interference fringes that are spaced in proportion to local skin friction. After a run the fringe spacings are imaged with a CCD-array digital camera and measured on a computer. Skin friction and transition measurements on a two-dimensional wing are presented and compared with computational predictions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-198814 , NAS 1.26:198814
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Boundary-layer transition and global skin friction measurement with an oil-fringe imaging technique (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new oil-fringe imaging fkin friction (FISF) technique to measure skin friction on wind tunnel models is presented. In the method used to demonstrate the technique, lines of oil are applied on surfaces that connect the intended sets of measurement points, and then a wind tunnel is run so that the oil thins and forms interference fringes that are spaced proportional to local skin friction. After a run the fringe spacings are imaged with a CCD-array digital camera and measured on a computer. Skin friction and transition measurements on a two-dimensional wing are presented and compared with computational predictions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: SAE PAPER 932550 , (ISSN 0148-7191); 15 p.|SAE, Aerotech ''93; Sep 27, 1993 - Sep 30, 1993; Costa Mesa, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Evolution of a Planar Wake in Adverse Pressure Gradient (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: In the interest of improving the predictability of high-lift systems at maximum lift conditions, a series of fundamental experiments were conducted to study the effects of adverse pressure gradient on a wake flow. Mean and fluctuating velocities were measured with a two-component laser-Doppler velocimeter. Data were obtained for several cases of adverse pressure gradient, producing flows ranging from no reversed flow to massively reversed flow. While the turbulent Reynolds stresses increase with increasing size of the reversed flow region, the gradient of Reynolds stress does not. Computations using various turbulence models were unable to reproduce the reversed flow.
    Keywords: Aerodynamics
    Type: NASA/TM-2016-219068 , ARC-E-DAA-TN29325
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Determination of Aerodynamic Characteristics of Bodies Free-Flying in a Wind Tunnel Using Data Telemetered from Onboard Instruments (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Total aerodynamic forces and moments of free flying body in wind tunnel determined from accelerations measured and telemetered by onboard instruments
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 66-775 , AIAA Aerodynamic Testing Conference; Sep 21, 1966 - Sep 23, 1966; Los Angeles, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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