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  • Inorganic Chemistry  (1.443)
  • AERODYNAMICS  (886)
  • Engineering
  • 1995-1999
  • 1975-1979  (2.641)
  • 1979  (1.419)
  • 1975  (1.222)
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  • 1995-1999
  • 1975-1979  (2.641)
Jahr
  • 1
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    On wings of circular design (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-75505
    Format: application/pdf
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  • 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
    Publikationsdatum: 2019-08-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-75732
    Format: application/pdf
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  • 3
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    Aircraft icing: Introduction (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Lewis Res. Center Aircraft Icing; 3 p
    Format: text
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  • 4
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    NASA research objectives and roles (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-28
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: 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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    Aeronautical Engineering: A special bibliography with indexes, supplement 55 (1975)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-27
    Beschreibung: This bibliography lists 260 reports, articles, and other documents introduced into the NASA scientific and technical information system in February 1975.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-SP-7037(55)
    Format: application/pdf
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  • 6
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    Approximation theory for boundary layer suction through individual slits (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-27
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-75384 , DVL-184
    Format: application/pdf
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  • 7
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    Modal Interpolation Program, L 215 (INTERP) (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-2848 , D6-44457
    Format: application/pdf
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  • 8
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    The Influence of Sweep on the Aerodynamic Loading of an Oscillating NACA0012 Airfoil (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-145350
    Format: application/pdf
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  • 9
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    Steady and Oscillatory, Subsonic and Supersonic, Aerodynamic Pressure and Generalized Forces for Complex Aircraft Configurations and Applications to Flutter (1975)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: A general method for analyzing aerodynamic flows around complex configurations is presented. By applying the Green function method, a linear integral equation relating the unknown, small perturbation potential on the surface of the body, to the known downwash is obtained. The surfaces of the aircraft, wake and diaphragm (if necessary) are divided into small quadrilateral elements which are approximated with hyperboloidal surfaces. The potential and its normal derivative are assumed to be constant within each element. This yields a set of linear algebraic equations and the coefficients are evaluated analytically. By using Gaussian elimination method, equations are solved for the potentials at the centroids of elements. The pressure coefficient is evaluated by the finite different method; the lift and moment coefficients are evaluated by numerical integration. Numerical results are presented, and applications to flutter are also included.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-142983
    Format: application/pdf
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  • 10
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    Vortex pattern development on the upper surface of a swept wing at high angle of attack (1979)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: 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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