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  • 1
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    Detailed transonic flow field measurements about a supercritical airfoil section (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The transonic flow field about a Whitcomb-type supercritical airfoil profile was measured in detail. In addition to the usual surface pressure distributions and wake surveys, schlieren photographs were taken and velocity vector profiles were determined in the upper surface boundary layer and in the near wake. Spanwise variations in the measured pressures were also determined. The data are analyzed with the aid of an inviscid transonic finite-difference computer program as well as with boundary layer modeling and calculation schemes.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3244 , A-5869
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An experimental study of transonic flow about a supercritical airfoil. Static pressure and drag data obtained from tests of a supercritical airfoil and an NACA 0012 airfoil at transonic speeds, supplement (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Surface static-pressure and drag data obtained from tests of two slightly modified versions of the original NASA Whitcomb airfoil and a model of the NACA 0012 airfoil section are presented. Data for the supercritical airfoil were obtained for a free-stream Mach number range of 0.5 to 0.9, and a chord Reynolds number range of 2 x 10 to the 6th power to 4 x 10 to the 6th power. The NACA 0012 airfoil was tested at a constant chord Reynolds number of 2 x 10 to the 6th power and a free-stream Mach number range of 0.6 to 0.8.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81336-SUPPL , A-8762 , NAS 1.15:81336-SUPPL
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    NASA TECHNICAL REPORTS
  • 3
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    Supercritical airfoil flowfield measurements (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Detailed measurements in the transonic flowfield about a Whitcomb-type supercritical airfoil profile are presented including surface pressure distributions, far wake surveys, spark schlieren photographs, and a series of vector velocity profiles in the boundary layer and in the near wake. A flowfield composite for the transonic drag rise condition is constructed from these data. The boundary layer measurements are compared with current correlation and computation schemes, and the importance of viscous thickening effects is demonstrated by the results of wave drag rise calculations for the thickened and unthickened profiles.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-880 , American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference; Jun 16, 1975 - Jun 18, 1975; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Control of boundary layer transition location and plate vibration in the presence of an external acoustic field (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The experiment is aimed at controlling the boundary layer transition location and the plate vibration when excited by a flow and an upstream sound source. Sound has been found to affect the flow at the leading edge and the response of a flexible plate in a boundary layer. Because the sound induces early transition, the panel vibration is acoustically coupled to the turbulent boundary layer by the upstream radiation. Localized surface heating at the leading edge delays the transition location downstream of the flexible plate. The response of the plate excited by a turbulent boundary layer (without sound) shows that the plate is forced to vibrate at different frequencies and with different amplitudes as the flow velocity changes indicating that the plate is driven by the convective waves of the boundary layer. The acoustic disturbances induced by the upstream sound dominate the response of the plate when the boundary layer is either turbulent or laminar. Active vibration control was used to reduce the sound induced displacement amplitude of the plate.
    Keywords: STRUCTURAL MECHANICS
    Type: In: Structural dynamics: Recent advances; Proceedings of the 4th International Conference, Univ. of Southampton, United Kingdom, July 15-18, 1991 (A93-45104 18-39); p. 702-711.
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  • 5
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    Structural deformation of an orthotropic plate (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Ring reinforcements for damping structural deformation in orthotropic mirror design
    Keywords: STRUCTURAL MECHANICS
    Type: NASA, WASHINGTON OPT. TELESCOPE TECHNOL. 1970; P 283-286
    Format: text
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  • 6
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    Measured transonic unsteady pressures on an energy efficient transport wing with oscillating control surfaces (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Highlight results are presented from subsonic and transonic pressure measurement studies conducted in the Langley Transonic Dynamics Tunnel on a supercritical wing model representative of an energy efficient transport design. Steady- and unsteady-pressure data were acquired on the upper and lower wing surface at an off-design Mach number of 0.60 and at the design Mach number of 0.78, for a Reynolds number of 2.2 x 10(6) (based on the wing average chord). The model configuration consisted of a sidewall-Mounted half-body fuselage and a semi-span wing with an aspect ratio of 10.76, a leading-edge sweepback angle of 28.8 degrees, and supercritical airfoil sections. The wing is instrumented with 252 static pressure orifices and 164 dynamic pressure gages. Model test variables included wing angle of attack, control-surface mean deflection angle, control-surface oscillating deflection angle and frequency, and phasing between oscillating leading-edge and trailing-edge controls when used together.
    Keywords: AERODYNAMICS
    Type: Advan. Aerodyn.: Selected NASA Res.; p 21-36
    Format: text
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  • 7
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    VICONOPT - Program for exact vibration and buckling analysis or design of prismatic plate assemblies (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA Journal (ISSN 0001-1452); 29; 1927
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  • 8
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    Exact Bernoulli-Euler static stiffness matrix for a range of tapered beam-columns (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The static stiffnesses for torsional and flexural deformation of a tapered beam under axial loading are determined analytically, extending the Bernoulli-Euler/Bessel-function approach of Banerjee and Williams (1985). The derivation of the expressions is explained in detail, and numerical results for sample problems are presented in tables and shown to be in excellent agreement with those obtained using stepped beams of 400 or 500 elements.
    Keywords: STRUCTURAL MECHANICS
    Type: International Journal for Numerical Methods in Engineering (ISSN 0029-5981); 23; 1615-162
    Format: text
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  • 9
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    Buckling of simply supported plate assemblies subject to shear loading (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An analysis is presented of the shear buckling load of an arbitrary simply-supported prismatic plate assembly or stiffened panel configuration. The method utilizes stiffness matrices developed by Wittrick (1968). For the restraint of simple support along edges perpendicular to the longitudinal direction, various wavelengths of response are combined using an energy method that involves only a boundary integral. Numerical results for plate and panel configurations show the accuracy and convergence of the method.
    Keywords: STRUCTURAL MECHANICS
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  • 10
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    Inclusion of elastically connected members in exact buckling and frequency calculations (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A standard stiffness matrix procedure which permits any combination of rigid, elastic, pinned or sliding connections of the degrees of freedom at the ends of a member to the nodes of its parent structure is described, in order to show how easily it can be extended to allow an existing algorithm to be used to ensure that no eigenvalues of the parent structure can be missed even when 'exact' member theory is used. The eigenvalues are the natural frequencies of undamped free vibration analyses or the critical load factors of buckling problems. The method preserves the exactness of the member theory and an efficient method for computer application is indicated. The theory also permits any combination of rigid, elastic, pinned or sliding connections between the freedoms of a substructure and those of its parent structure.
    Keywords: STRUCTURAL MECHANICS
    Type: Computers and Structures (ISSN 0045-7949); 22; 3, 19
    Format: text
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