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  • Inorganic Chemistry  (720)
  • AERODYNAMICS  (471)
  • Engineering
  • 1995-1999
  • 1975-1979  (1,419)
  • 1979  (1,419)
Collection
Keywords
Publisher
Years
  • 1995-1999
  • 1975-1979  (1,419)
Year
  • 1
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    On wings of circular design (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Prandtl's method of sources and sinks for air foils is used to investigate the aerodynamics of circular wings in constant flow. Lift distribution, total lift, and pitching moment are investigated as well as the influence of changes in the angle of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75505
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Solution of a few nonlinear problems in aerodynamics by the finite elements and functional least squares methods (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The numerical simulation of the transonic flows of idealized fluids and of incompressible viscous fluids, by the nonlinear least squares methods is presented. The nonlinear equations, the boundary conditions, and the various constraints controlling the two types of flow are described. The standard iterative methods for solving a quasi elliptical nonlinear equation with partial derivatives are reviewed with emphasis placed on two examples: the fixed point method applied to the Gelder functional in the case of compressible subsonic flows and the Newton method used in the technique of decomposition of the lifting potential. The new abstract least squares method is discussed. It consists of substituting the nonlinear equation by a problem of minimization in a H to the minus 1 type Sobolev functional space.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75732
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aircraft icing: Introduction (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The objectives of the Workshop were as follows: (1) to assess the current understanding of fixed wing and rotorcraft operational icing environments and problems (2) to evaluate facilities requirements for R&D and certification purposes (3) to examine means of improving icing forecasts (4) to identify shortcomings in aeronautical icing knowledge which can be alleviated by new research and instrumentation development.
    Keywords: AERODYNAMICS
    Type: NASA. Lewis Res. Center Aircraft Icing; 3 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    NASA research objectives and roles (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A chronology of airfoil development is presented in order to put the present NASA airfoil program in perspective. The impact of the NACA series airfoils is considered. Development of advanced analytical and experimental methods for the design and for the determination of the characteristics of not only single element airfoils, but of multielement airfoil combinations used in aerodynamic controls and high lift systems is emphasized along with applications.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1 Pt 1; p 1-9
    Format: application/pdf
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  • 5
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    Approximation theory for boundary layer suction through individual slits (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The basic concepts of influencing boundary layers are summarized, especially the prevention of flow detachment and the reduction of frictional resistance. A mathematical analysis of suction through a slit is presented with two parameters, for thickness and for shape of the boundary layer, being introduced to specify the flow's velocity profile behind the slit. An approximation of the shape parameter produces a useful formula, which can be used to determine the most favorable position of the slit. An aerodynamic example is given.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75384 , DVL-184
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Modal Interpolation Program, L 215 (INTERP) (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The design, structure, and usage of the modal interpolation program L215 are presented. The program uses modal data sets of arrays containing interpolation coefficients. The interpolation arrays are used to determine displacements at various aerodynamic control points. The displacements consist of translations normal to the aerodynamic surface and surface slopes that are parallel and perpendicular to the free stream direction. Five different interpolation methods are available.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2848 , D6-44457
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The Influence of Sweep on the Aerodynamic Loading of an Oscillating NACA0012 Airfoil (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The effect of sweep on the dynamic response of the NACA 0012 airfoil was investigated. Unsteady chordwise distributed pressure data were obtained from a tunnel spanning wing equipped with 21 single surface transducers (13 on the suction side and 8 on the pressure side of the airfoil). The pressure data were obtained at pitching amplitudes of 8 and 10 degrees over a tunnel Mach number range of 0.10 to 0.46 and a pitching frequency range of 2.5 to 10.6 cycles per second. The wing was oscillated in the unswept and swept positions about the quarter-chord pivot axis relative to mean incidence angle settings of 0, 9, 12, and 15 degrees. A compilation of all the response data obtained during the test program is presented. These data are in the form of normal force, chord force, lift force, pressure drag, and moment hysteresis loops derived from chordwise integrations of the unsteady pressure distributions. The hysteresis loops are organized in two main sections. In the first section, the loop data are arranged to show the effect of sweep (lambda = 0 and 30 deg) for all available combinations of mean incidence angle, pitching amplitude, reduced frequency, and chordwise Mach number. The second section shows the effect of chordwise Mach number (MC = 0.30 and MC = 0.40) on the swept wing response for all available combinations of mean incidence angle, pitching amplitude, and reduced frequency.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145350
    Format: application/pdf
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  • 8
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    Vortex pattern development on the upper surface of a swept wing at high angle of attack (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: An experimental study, based on a swept wing, was undertaken in the water tunnel and the wind tunnel at low speeds, with a view to improving the understanding of the intervening phenomena and to make easier their modelling. The vortex flow effects on the wing are first illustrated from global effort measurements and static pressure distributions. The domain of existence of this type of flow is deduced as a function of both sweep angle and angle of attack. By a phenomenological study in the water tunnel, an attempt is made to describe the physical pattern of the vortex flow, from its formation near the apex to its breakdown at the trailing edge. Lastly, by means of a clinometric probe, the flow field over the wing is determined.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75377 , ONERA-TP-1978-124 , MEMOIRE-12 , AGARD. Reunion sur l''Aerodynamique des Grandes Incidences; Oct 04, 1978 - Oct 06, 1978; Sandefjord; Norway
    Format: application/pdf
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  • 9
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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
  • 10
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    Effects of probe shape change on flow phenomena during Jovian entry (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The effects of probe shape change on the flow phenomena around a Jovian entry body is investigated. The initial body shapes considered are: 45-degree sphere cone, 35-degree hyperboloid, and 45-degree ellipsoid. The radiating shock-layer flow is assumed to be axisymmetric, inviscid, and in chemical and local thermodynamic equilibrium. The radiative transfer is calculated with an existing nongray radiation model that accounts for molecular band, atomic line, and continuum transitions. The results indicate that the shock-standoff distance, shock temperature and density, wall pressure distribution and radiative heating to the body are influenced significantly because of the probe shape change. The effect of shape change on radiative heating of the afterbody was considerably larger for the sphere cone and ellipsoid than for the hyperboloid. For the peak heating conditions, the net radiative heating to the body was found to be highest for the ellipsoid
    Keywords: AERODYNAMICS
    Type: IAF PAPER 79-43 , International Astronautical Federation, International Astronautical Congress; Sept. 17-22, 1979; Munich
    Format: text
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