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  • AERODYNAMICS  (2,110)
  • 1975-1979  (2,110)
  • 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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  • 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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  • 4
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    Lee surface flow phenomena over Space Shuttle at large angles of attack at M infinity = 6 (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An investigation was conducted regarding the surface heat transfer on the leeward side of the Space Shuttle, taking into account different free stream Reynolds numbers and angles of attack. Another investigation was concerned with the peak heating due to boundary layer transition and flow separation in the case of different Space Shuttle configurations. Criteria for vortex generation on the leeward flow were also examined along with the effect of transition on vortex generation. Attention was given to the leeward flowfield in the vortex flow region and the method of constructing an equivalent model for leeward flowfield analysis.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-148 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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  • 5
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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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  • 6
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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
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  • 7
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    Inviscid transonic flow computations with shock fitting (1976)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: First- and second-order numerical procedures for calculating two-dimensional transonic flows that treat shock waves as discontinuities are discussed. This short communication illustrates their application to a simple but non-trivial problem for which there are limited theoretical results.
    Keywords: AERODYNAMICS
    Type: Symposium Transsonicum II; Sep 08, 1975 - Sep 13, 1975; Goettingen
    Format: text
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  • 8
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    Unsteady transonic flow computations (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The numerical procedures previously developed for computing nonlinear and time-linearized small-perturbation unsteady transonic flows are briefly reviewed, and the effects of unsteady modes of motion on two-dimensional transonic flows are evaluated. The numerical procedure used comprises an alternating-direction implicit scheme and treats shock waves as discontinuities in the flow. Comparison of the time-linearized results with fully nonlinear calculations delineates their range of applicability. The unsteady behavior due to harmonic pitching and flap oscillations of an NACA airfoil is also examined.
    Keywords: AERODYNAMICS
    Type: Symposium on Unsteady Aerodynamics; Sept. 26-28, 1977; Ottawa; Canada
    Format: text
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  • 9
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    Effects of deflected thrust on the longitudinal aerodynamic characteristics of a close-coupled wing-canard configuration (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of power on the longitudinal aerodynamic characteristics of a close-coupled wing-canard fighter configuration with partial-span rectangular nozzles at the trailing edge of the wing were investigated. Data were obtained on a basic wing-strake configuration for nozzle and flap deflections from 0 deg to 30 deg and for nominal thrust coefficients from 0 to 0.30. The model was tested over an angle-of-attack range from -2 deg to 40 deg at Mach numbers of 0.15 and 0.18. Results show substantial improvements in lift-curve slope, in maximum lift, and in drag-due-to-lift efficiency when the canard and strakes have been added to the basic wing-fuselage (wing-alone) configuration. Addition of power increased both lift-curve slope and maximum lift, improved longitudinal stability, and reduced drag due to lift on both the wing-canard and wing-canard-strake configurations. These beneficial effects are primarily derived from boundary-layer control due to moderate thrust coefficients which delay flow separation on the nozzle and inboard portion of the wing flaps.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1090 , L-11886
    Format: application/pdf
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  • 10
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    Effects of spanwise nozzle geometry and location on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration at subsonic speeds (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A V/STOL tunnel study was performed to determine the effects of spanwise blowing on longitudinal aerodynamic characteristics of a model using a vectored-over-wing powered lift concept. The effects of spanwise nozzle throat area, internal and external nozzle geometry, and vertical and axial location were investigated. These effects were studied at a Mach number of 0.186 over an angle-of-attack range from 14 deg to 40 deg. A high pressure air system was used to provide jet-exhaust simulation. Engine nozzle pressure ratio was varied from 1.0 (jet off) to approximately 3.75.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1215 , L-12015
    Format: application/pdf
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