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  • Other Sources  (3,223)
  • AERODYNAMICS  (2,110)
  • FLUID MECHANICS AND HEAT TRANSFER  (1,113)
  • 2020-2022
  • 1975-1979  (3,223)
  • 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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  • 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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  • 3
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    First results of a study on turbulent boundary layers in oscillating flow with a mean adverse pressure gradient (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The development of a turbulent unsteady boundary layer with a mean pressure gradient strong enough to induce separation, in order to complete the extend results obtained for the flat plate configuration is presented. The longitudinal component of the velocity is measured using constant temperature hot wire anemometer. The region where negative velocities exist is investigated with a laser Doppler velocimeter system with BRAGG cells. The boundary layer responds by forced pulsation to the perturbation of potential flow. The unsteady effects observed are very important. The average location of the zero skin friction point moves periodically at the perturbation frequency. Average velocity profiles from different instants in the cycle are compared. The existence of a logarithmic region enables a simple calculation of the maximum phase shift of the velocity in the boundary layer. An attempt of calculation by an integral method of boundary layer development is presented, up to the point where reverse flow starts appearing.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-75799 , Colloq. d''Aerodyn. Appl.; Nov 07, 1978 - Nov 09, 1978; Marseille
    Format: application/pdf
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  • 4
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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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  • 5
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    Practical calculation of laminar and turbulent bled-off boundary layers (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Bleed-off of boundary layer material is shown to be an effective means for reducing drag by conserving the laminar boundary layer and preventing separation of the turbulent boundary layer. The case in which the two effects of bleed-off overlap is examined. Empirical methods are extended to the case of bleed-off. Laminar and turbulent boundary layers are treated simultaneously and the approximation differential equations are solved without an uncertain error. The case without bleed-off is also treated.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75328
    Format: application/pdf
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  • 6
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    Studies on the influence on flexural wall deformations on the development of the flow boundary layer (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Flexural wave-like deformations can be used to excite boundary layer waves which in turn lead to the onset of turbulence in the boundary layer. The investigations were performed with flow velocities between 5 m/s and 40 m/s. With four different flexural wave transmissions a frequency range from 0.2 kc/s to 1.5 kc/s and a phase velocity range from 3.5 m/s to 12 m/s was covered. The excitation of boundary layer waves becomes most effective if the phase velocity of the flexural wave coincides with the phase velocity region of unstable boundary layer waves.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-75220
    Format: application/pdf
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  • 7
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    Effect of the properties of a porous coating on boundary layer stability (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Drawing off gas from the boundary layer is a well-known method for increasing the stability of boundary layers. The increase in stability is primarily connected with a change in the velocity profile form in the case of suction. On the basis of the assumption that the velocity perturbations on a porous slate do not equal zero, the influence of the properties of a permeable surface upon the boundary layer stability were studied.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75235
    Format: application/pdf
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  • 8
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    Experimental studies on the influence of the degree of turbulence and of a turbulence thread on the compressible subsonic flow through flat compressor cascades (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The measurements revealed that at low Reynolds numbers the profile loss is considerably reduced both by the increased degree of turbulence and by a turbulence thread, while it is somewhat increased at high Reynolds numbers, and that a profile loss reduction is connected with an increase in deflection and in pressure shift. The turbulence generator is most effective on the one hand in the middle of the operating range of the cascades, and on the other at very high Mach numbers together with a large angle of incidence.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75276
    Format: application/pdf
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  • 9
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    A finite volume method for calculating transonic potential flow around wings from the pressure minimum integral (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Analysis of the pressure minimum integral in the calculation of three-dimensional potential flow around wings makes it possible to use non-rectangular mesh networks for distributing the three-dimensional potential into discrete points. The method is comparatively easily expanded to the treatment of realistic airplane configurations. Shock-pressure affected pressure distributions on any wings are determined with accuracy using this method.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75324
    Format: application/pdf
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  • 10
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    Measurement of the turbulence intensity behind a two-dimensional cascade and in a three-stage axial blower (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Turbulence intensity (Tu) measurements were made in two-dimensional and rotating cascades of blades in a low-speed cascade wind tunnel using hot-wire probes as sensors. The local Tu at Re = 1.6x100000 was determined in the wake zone behind a two-dimensional cascade. Then the values were recomputed for a rotating cascade, giving a mean turbulence intensity of 6.5% at 1/10 chord downstream and 2.9% at one chord. Fans were used for measurements on the rotating cascade. Re was equal to 7x100000. Frequency analysis was employed to separate the actual Tu of the entry flow from the effects caused by interaction with the rotor blades, showing that the true Tu increased from a few tenths of a percent to 6.6% in the 1st rotor, and from 7.2 to 9.3% in the 2d rotor. The Tu behind the 3d rotor was equal to 8.9%.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75275
    Format: application/pdf
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