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  • AERODYNAMICS  (471)
  • 1975-1979  (471)
  • 1925-1929
  • 1979  (471)
  • 1
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    A new flow model for highly separated airfoil flows at low speeds (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An analytical model for separated airfoil flows is presented which is based on experimentally observed physical phenomena. These include a free stagnation point aft of the airfoil and a standing vortex in the separated region. A computer program is described which iteratively matches the outer potential flow, the airfoil turbulent boundary layer, the separated jet entrainment, mass conservation in the separated bubble, and the rear stagnation pressure. Separation location and pressure are not specified a priori. Results are presented for surface pressure coefficient and compared with experiment for three angles of attack for a GA(W)-1, 17% thick airfoil.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 1; p 367-382
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Approximate convective heating equations for hypersonic flows (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Laminar and turbulent heating-rate equations appropriate for engineering predictions of the convective heating rates about blunt reentry spacecraft at hypersonic conditions are developed. The approximate methods are applicable to both nonreacting and reacting gas mixtures for either constant or variable-entropy edge conditions. A procedure which accounts for variable-entropy effects and is not based on mass balancing is presented. Results of the approximate heating methods are in good agreement with existing experimental results as well as boundary-layer and viscous-shock-layer solutions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-1078 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; Jun 04, 1979 - Jun 06, 1979; Orlando, FL
    Format: text
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  • 3
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    The significance of wing end configuration in airfoil design for civil aviation aircraft (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Lift-dependent induced drag in commercial aviation aircraft is discussed, with emphasis on the necessary compromises between wing and configuration modifications which better lift performance and the weight gains accompanying such modifications. Triangular, rectangular and elliptical configurations for wing ends are considered; attention is also given to airfoil designs incorporating winglets. Water tunnel tests of several configurations are reported. In addition, applications of wing and modifications to advanced technology commercial aviation aircraft and the Airbus A-300 are mentioned.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75711 , PAPER-77-030
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Flow and Force Equations for a Body Revolving in a Fluid (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A general method for finding the steady flow velocity relative to a body in plane curvilinear motion, whence the pressure is found by Bernoulli's energy principle is described. Integration of the pressure supplies basic formulas for the zonal forces and moments on the revolving body. The application of the steady flow method for calculating the velocity and pressure at all points of the flow inside and outside an ellipsoid and some of its limiting forms is presented and graphs those quantities for the latter forms. In some useful cases experimental pressures are plotted for comparison with theoretical. The pressure, and thence the zonal force and moment, on hulls in plane curvilinear flight are calculated. General equations for the resultant fluid forces and moments on trisymmetrical bodies moving through a perfect fluid are derived. Formulas for potential coefficients and inertia coefficients for an ellipsoid and its limiting forms are presented.
    Keywords: AERODYNAMICS
    Type: NACA-TR-323 , NASA. Ames Res. Center Classical Aerodyn. Theory; p 197-235
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  • 5
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    Flow and Drag Formulas for Simple Quadrics (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The pressure distribution and resistance found by theory and experiment for simple quadrics fixed in an infinite uniform stream of practically incompressible fluid are calculated. The experimental values pertain to air and some liquids, especially water; the theoretical refer sometimes to perfect, again to viscid fluids. Formulas for the velocity at all points of the flow field are given. Pressure and pressure drag are discussed for a sphere, a round cylinder, the elliptic cylinder, the prolate and oblate spheroid, and the circular disk. The velocity and pressure in an oblique flow are examined.
    Keywords: AERODYNAMICS
    Type: NACA-TR-253 , NASA. Ames Res. Center Classical Aerodyn. Theory; p 175-196
    Format: application/pdf
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  • 6
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    Low-speed wind-tunnel tests of a 1/10-scale model of an advanced arrow-wing supersonic cruise configuration designed for cruise at Mach 2.2 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The low-speed longitudinal and lateral-directional characteristics of a scale model of an advanced arrow-wing supersonic cruise configuration were investigated in tests conducted at a Reynolds number of 4.19 x 10 to the 6th power based on the mean aerodynamic chord, with an angle of attack range from - 6 deg to 23 deg and sideslip angle range from -15 deg to 20 deg. The effects of segmented leading-edge flaps, slotted trailing-edge flaps, horizontal and vertical tails, and ailerons and spoilers were determined. Extensive pressure data and flow visualization pictures with non-intrusive fluorescent mini-tufts were obtained.
    Keywords: AERODYNAMICS
    Type: NASA-TM-80152
    Format: application/pdf
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  • 7
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    Griffith diffusers (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Contoured wall diffusers are designed by using an inverse method. The prescribed wall velocity distribution(s) was taken from the high lift airfoil designed by A. A. Griffith in 1938; therefore, such diffusers are named Griffith diffusers. First the formulation of the inverse problem and the method of solution are outlined. Then the typical contour of a two-dimensional diffuser and velocity distributions across the flow channel at various stations are presented. For a Griffith diffuser to operate as it is designed, boundary layer suction is necessary. Discussion of the percentage of through-flow required to be removed for the purpose of boundary layer control is given. Finally, reference is made to the latest version of a computer program for a two-dimensional diffuser requiring only area ratio, nondimensional length and suction percentage as inputs.
    Keywords: AERODYNAMICS
    Format: text
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  • 8
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    Considerations of some critical ejector problems (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Some aspects of ejector design and application, including, three dimensional effects and cross flow effects are presented.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Workshop on Thrust Augmenting Ejectors; p 363-384
    Format: application/pdf
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  • 9
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    Internal-external flow integration for a thin ejector-flapped wing section (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Thin airfoil theories of an ejector flapped wing section are reviewed. The global matching of the external airfoil flow with the ejector internal flow and the overall ejector flapped wing section aerodynamic performance are examined. Mathematical models of the external and internal flows are presented. The delineation of the suction flow coefficient characteristics are discussed. The idealized lift performance of an ejector flapped wing relative to a jet augmented flapped wing are compared.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Workshop on Thrust Augmenting
    Format: application/pdf
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  • 10
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    The supersonic triplet - A new aerodynamic panel singularity with directional properties (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new supersonic triplet singularity has been developed which eliminates internal waves generated by panels having supersonic edges. The triplet is a linear combination of source and vortex distributions which provides the desired directional properties in the flow field surrounding the panel. The theoretical development of the triplet is described, together with its application to the calculation of surface pressure on arbitrary body shapes. Examples are presented comparing the results of the new method with other supersonic panel methods and with experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0273 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
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