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  • FLUID MECHANICS  (34)
  • 1980-1984
  • 1970-1974  (34)
  • 1974  (34)
  • 1
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    Turbulent vortex streets and the entrainment mechanism of the turbulent wake (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The results of an experimental investigation of a turbulent vortex street in the range from 1000 to 20,000 are presented. The vortex street was created by the motion of a circular cylinder in a motionless fluid (mercury). Photographs obtained showed that the turbulent street, created by the vortex shedding behind the cylinder, persisted at longer downstream distances and higher Reynolds numbers than previously reported in the literature. A theory was developed to account for the experimental measurements pertaining to the change of the geometrical characteristics, (the distance between the two rows of vortices and the longitudinal distance between two consecutive vortices on the same row), of the street in the downstream direction. The implications of the structure of the vortex street on the entrainment mechanism of the turbulent wake are discussed.
    Keywords: FLUID MECHANICS
    Type: Journal of Fluid Mechanics; 62; Jan. 8
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Model wall and recovery temperature effects on experimental heat transfer data analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Basic analytical procedures are used to illustrate, both qualitatively and quantitatively, the relative impact upon heat transfer data analysis of certain factors which may affect the accuracy of experimental heat transfer data. Inaccurate knowledge of adiabatic wall conditions results in a corresponding inaccuracy in the measured heat transfer coefficient. The magnitude of the resulting error is extreme for data obtained at wall temperatures approaching the adiabatic condition. High model wall temperatures and wall temperature gradients affect the level and distribution of heat transfer to an experimental model. The significance of each of these factors is examined and its impact upon heat transfer data analysis is assessed.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-71967
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flow studies in a wet steam turbine (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The design and test results of a four stage wet vapor turbine operating with slightly superheated inlet steam and expanding to 10% exit moisture are presented. High speed movies at 3000 frames per second of liquid movement on the pressure side and along the trailing edge of the last stator blade are discussed along with back lighted photographs of moisture drops as they were torn from the stator blade trailing edge. Movies at lower framing rates were also taken of the exit of the last rotating blade and the casing moisture removal slot located in line with the rotor blade shroud. Also moisture removal data are presented of casing slot removal at the exit of the third and fourth rotor blades and for slots located in the trailing edge of the last stator blade. Finally, the degradation of turbine thermodynamic performance due to condensation formation and movement is discussed.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-134683 , WANL-13230F
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Method for producing a uniform, low Reynolds number jet (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: In one attempt to produce a simple inexpensive nozzle, a 2-in. diam plate with 37 holes was investigated (Stadler, 1960), anticipating that the small jets emanating from the plate would combine to form a uniform stream. This experiment was unsuccessful because a uniform flow was not established until the flow had progressed many nozzle diameters downstream. However, an extension of this concept to a much larger number of very small jets, viz., a porous plate, did provide a method for producing a uniform, low Reynolds number jet almost immediately downstream of the nozzle (Greene, 1973). The method is described and some typical jet velocity profiles for nozzle Reynolds numbers from 50 to 1000 are given.
    Keywords: FLUID MECHANICS
    Type: Journal of Spacecraft and Rockets; 11; Aug. 197
    Format: text
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  • 5
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    Wall shear in strongly retarded and separated compressible turbulent boundary layers (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: FLUID MECHANICS
    Type: AIAA Journal; 12; Oct. 197
    Format: text
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  • 6
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    The application of Riegels' rule and time-like damping to transonic flow calculations (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Finite difference relaxation solutions of the nonlinear small perturbation equations have proven reliable and successful in determining the transonic flowfields about thin airfoils. However, application of the small perturbation approach to thick airfoils usually results in an accuracy less than desirable. The incorporation of Riegels' Rule and time-like damping into the small perturbation approach and their application to thick and thin airfoils in transonic flow are discussed. Studies for thick and thin airfoils are presented. It is concluded that Riegels' Rule and damping should both be included in small perturbation transonic flow calculations.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-138181 , TAMRF-3033-7401 , AIAA Southwestern Student Paper Competition; Arlington, TX; United States
    Format: application/pdf
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  • 7
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    Nonlinear cellular motions in Poiseuille channel flow (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: In a number of nonlinear solutions to the equations of channel flow the velocity is decomposed into a mean part plus a nonlinear disturbance. The idea that nonlinear effects place a limitation on the amplitudes of the disturbance flow is considered. In the reported investigation the disturbance flow is represented by drastically limited Fourier expansions in the downstream coordinate. The resulting equations are solved numerically with high accuracy to obtain a good representation of the cross-stream structure of the solution. The results of the investigation show that indeed the nonlinear terms always limit the amplitude of the disturbance flow in this approximation.
    Keywords: FLUID MECHANICS
    Type: Journal of Fluid Mechanics; 64; June 19
    Format: text
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  • 8
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    Comparison of interference-free numerical results with sample experimental data for the AEDC wall-interference model at transonic and subsonic flow conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Numerical results obtained from two computer programs recently developed with NASA support and now available for use by others are compared with some sample experimental data taken on a rectangular-wing configuration in the AEDC 16-Foot Transonic Tunnel at transonic and subsonic flow conditions. This data was used in an AEDC investigation as reference data to deduce the tunnel-wall interference effects for corresponding data taken in a smaller tunnel. The comparisons were originally intended to see how well a current state-of-the-art transonic flow calculation for a simple 3-D wing agreed with data which was felt by experimentalists to be relatively interference-free. As a result of the discrepancies between the experimental data and computational results at the quoted angle of attack, it was then deduced from an approximate stress analysis that the sting had deflected appreciably. Thus, the comparisons themselves are not so meaningful, since the calculations must be repeated at the proper angle of attack. Of more importance, however, is a demonstration of the utility of currently available computational tools in the analysis and correlation of transonic experimental data.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-71991
    Format: application/pdf
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  • 9
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    An experimental and theoretical study of the flow phenomena within a vortex sink rate sensor (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted to obtain a description of the flow field within a vortex sink rate sensor and to observe the influence of viscous effects on its performance. The characteristics of the sensor are described. The method for conducting the test is reported. It was determined that for a specific mass flow rate and the geometry of the vortex chamber, the flow in the vortex chamber was only affected, locally, by the size of the sink tube diameter. Within the sink tube, all three velocity components were found to be higher for the small sink tube diameters. As the speed of rotation of the sensor was increased, the tangential velocities within the vortex chamber, as well as in the sink tube, increased in proportion to the speed of rotation.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-139648 , TR-74-T2
    Format: application/pdf
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  • 10
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    A modified Newton-Raphson analysis of flight measurements of the trailing vortices of a heavy jet transport (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A modified Newton-Raphson method has been used to determine the parameters in equations describing the vortex flow to obtain a best match with flight measurements of the flow behind the C-5A airplane. The flight measurements were made using a specially instrumented T-33 airplane which passed as closely as possible to the centers of the trailing vortices at several distances behind the C-5A airplane. The flight measurements were transformed to flow velocity relative to an inertial frame of reference. The assumed form of the flow consisted of the superposition of two counterrotating, finite core vortices. The positions of the vortex centers, their total circulation, the effective eddy viscosity and measurement bias were the parameters adjusted. The assumed form of vortex flow fit well the measured velocities for the numerous sets of data, both flaps up and down for the C-5A airplane. The resulting values of total circulation, however, were about two-thirds that expected of a wing with an elliptical loading. A partial explanation of the less than expected circulation is a dip in the spanwise lift distribution at the airplane's center line. The distance between the trailing vortices at the smallest times encountered is somewhat less than that expected for an elliptical wing loading.
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-7404 , L-8838
    Format: application/pdf
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