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  • 1
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    An improved viscid/inviscid interaction procedure for transonic flow over airfoils (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new interacting boundary layer approach for computing the viscous transonic flow over airfoils is described. The theory includes a complete treatment of viscous interaction effects induced by the wake and accounts for normal pressure gradient effects across the boundary layer near trailing edges. The method is based on systematic expansions of the full Reynolds equation of turbulent flow in the limit of Reynolds numbers, Reynolds infinity. Procedures are developed for incorporating the local trailing edge solution into the numerical solution of the coupled full potential and integral boundary layer equations. Although the theory is strictly applicable to airfoils with cusped or nearly cusped trailing edges and to turbulent boundary layers that remain fully attached to the airfoil surface, the method was successfully applied to more general airfoils and to flows with small separation zones. Comparisons of theoretical solutions with wind tunnel data indicate the present method can accurately predict the section characteristics of airfoils including the absolute levels of drag.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3805 , NAS 1.26:3805 , RE-682
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Application of numerical optimization to the design of advanced supercritical airfoils (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An application of numerical optimization to the design of advanced airfoils for transonic aircraft showed that low-drag sections can be developed for a given design Mach number without an accompanying drag increase at lower Mach numbers. This is achieved by imposing a constraint on the drag coefficient at an off-design Mach number while minimizing the drag coefficient at the design Mach number. This multiple design-point numerical optimization has been implemented with the use of airfoil shape functions which permit a wide range of attainable profiles during the optimization process. Analytical data for the starting airfoil shape, a single design-point optimized shape, and a double design-point optimized shape are presented. Experimental data obtained in the NASA Ames two-by two-foot wind tunnel are also presented and discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 1; p 315-325
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Wake vortex technology (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A brief overview of the highlights of NASA's wake vortex minimization program is presented. The significant results of this program are summarized as follows: (1) it is technically feasible to reduce significantly the rolling upset created on a trailing aircraft; (2) the basic principles or methods by which reduction in the vortex strength can be achieved have been identified; and (3) an analytical capability for investigating aircraft vortex wakes has been developed.
    Keywords: AERODYNAMICS
    Type: CTOL Transport Technol., 1978; p 757-771
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    In-flight measurements of wing ice shapes and wing section drag increases caused by natural icing conditions (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aircraft icing flight research was performed in natural icing conditions with a twin engine computer type STOL aircraft. In-flight measurements were made of the icing cloud environment, the shape of the ice accretion on the wing, and the corresponding increase in the wing section drag. Results are presented for three icing encounters. On one flight, the wing section drag coefficient increased 35 percent over the uniced baseline for cruise conditions while a 43 percent increase was observed at an aircraft angle of attack of 6.2 degrees.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87301 , E-3013 , NAS 1.15:87301
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Viscous wing theory development. Volume 1: Analysis, method and results (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Viscous transonic flows at large Reynolds numbers over 3-D wings were analyzed using a zonal viscid-inviscid interaction approach. A new numerical AFZ scheme was developed in conjunction with the finite volume formulation for the solution of the inviscid full-potential equation. A special far-field asymptotic boundary condition was developed and a second-order artificial viscosity included for an improved inviscid solution methodology. The integral method was used for the laminar/turbulent boundary layer and 3-D viscous wake calculation. The interaction calculation included the coupling conditions of the source flux due to the wing surface boundary layer, the flux jump due to the viscous wake, and the wake curvature effect. A method was also devised incorporating the 2-D trailing edge strong interaction solution for the normal pressure correction near the trailing edge region. A fully automated computer program was developed to perform the proposed method with one scalar version to be used on an IBM-3081 and two vectorized versions on Cray-1 and Cyber-205 computers.
    Keywords: AERODYNAMICS
    Type: NASA-CR-178156 , NAS 1.26:178156 , RE-725-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Double-branched vortex generator (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to assess the suitability of using a double branched vortex generator in parametric studies involving vortex interactions, an experimental study of the main vortex and secondary flows produced by a double branched vortex generator was conducted in a 20-by-40 cm indraft wind tunnel. Measurements of the cross flow velocities were made with a five hole pressure probe from which vorticity contours and vortex parameters were derived. The results showed that the optimum configuration consisted of chord extensions with the absence of a centerbody.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88201 , REPT-86064 , NAS 1.15:88201
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Applications of an adaptive unstructured solution algorithm to the analysis of high speed flows (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An upwind cell-centered scheme for the solution of steady laminar viscous high-speed flows is implemented on unstructured two-dimensional meshes. The first-order implementation employs Roe's (1981) approximate Riemann solver, and a higher-order extension is produced by using linear reconstruction with limiting. The procedure is applied to the solution of inviscid subsonic flow over an airfoil, inviscid supersonic flow past a cylinder, and viscous hypersonic flow past a double ellipse. A detailed study is then made of a hypersonic laminar viscous flow on a 24-deg compression corner. It is shown that good agreement is achieved with previous predictions using finite-difference and finite-volume schemes. However, these predictions do not agree with experimental observations. With refinement of the structured grid at the leading edge, good agreement with experimental observations for the distributions of wall pressure, heating rate and skin friction is obtained.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0395
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Drag measurements at low lift of a four- nacelle airplane configuration having a longitudinal distribution of cross-sectional area conductive to low transonic drag rise (1953)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise
    Keywords: AERODYNAMICS
    Type: NACA-RM-L53E29
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Performance of a straight stator and a tilted stator tested with a high-solidity high-pressure-ratio transonic rotor (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Overall stage and stator blade element performance with straight stator and tilted stator in transonic axial flow compressor stage
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-99
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Heat transfer below reattaching turbulent flows. (1965)
    In:  Other Sources
    Details
    Publication Date: 2019-05-30
    Description: Base heating of launch vehicles examined by studying heat transfer processes in two- dimensional recirculation zone behind blunt trailing edge in Mach 3 wind tunnel
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 65-825
    Format: text
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