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  • AIRCRAFT PROPULSION AND POWER  (38)
  • FLUID MECHANICS AND HEAT TRANSFER  (38)
  • GENERAL
  • 1975-1979  (80)
  • 1976  (80)
  • 1
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    An experimental and computational investigation of the flow field about a transonic airfoil in supercritical flow with turbulent boundary-layer separation (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A combined experimental and computational research program is described for testing and guiding turbulence modeling within regions of separation induced by shock waves incident in turbulent boundary layers. Specifically, studies are made of the separated flow the rear portion of an 18%-thick circular-arc airfoil at zero angle of attack in high Reynolds number supercritical flow. The measurements include distributions of surface static pressure and local skin friction. The instruments employed include highfrequency response pressure cells and a large array of surface hot-wire skin-friction gages. Computations at the experimental flow conditions are made using time-dependent solutions of ensemble-averaged Navier-Stokes equations, plus additional equations for the turbulence modeling.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-X-73157 , A-6690
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Cold-air annular-cascade investigation of aerodynamic performance of core-engine-cooled turbine vanes. 2: Pressure surface trailing edge ejection and split trailing edge ejection (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic performance of two trailing edge ejection cooling configurations of a core-engine stator vane were experimentally determined in an ambient inlet-air full-annular cascade where three-dimensional effects could be obtained. The tests were conducted at the design mean-radius ideal aftermixed critical velocity ratio of 0.778. Overall vane aftermixed thermodynamic and primary efficiencies were obtained over a range of coolant flows to about 10 percent of the primary flow at a primary to coolant total temperature ratio of 1.0. The radial variation in efficiency and the circumferential and radial variations in vane-exit total pressure were determined. Comparisons are made with the solid (uncooled) vane.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3369 , E-8566
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An analytical study of reduced-gravity flow dynamics (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Addition of surface tension forces to a marker-and-cell code and the performance of four incompressible fluid simulations in reduced gravity, were studied. This marker-and-cell code has a variable grid capability with arbitrary curved boundaries and time dependent acceleration fields. The surface tension logic includes a spline fit of surface marker particles as well as contact angle logic for straight and curved wall boundaries. Three types of flow motion were simulated with the improved code: impulsive settling in a model Centaur LH2 tank, continuous settling in a model and full scale Centaur LO2 tank and mixing in a Centaur LH2 tank. The impulsive settling case confirmed a drop tower analysis which indicated more orderly fluid collection flow patterns with this method providing a potential savings in settling propellants. In the LO2 tank, fluid collection and flow simulation into the thrust barrel were achieved. The mixing simulation produced good results indicating both the development of the flow field and fluid interface behavior.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-135023 , CASD-NAS-76-015
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Noise reduction as affected by the extent and distribution of acoustic treatment in a turbofan engine inlet (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An inlet noise suppressor for a TF-34 engine designed to have three acoustically treated rings was tested with several different ring arrangements. The configurations included: all three rings; two outer rings; single outer ring; single intermediate ring, and finally no rings. It was expected that as rings were removed, the acoustic performance would be degraded considerably. While a degradation occurred, it was not as large as predictions indicated. In fact, the prediction showed good agreement with the data only for the full-ring inlet configuration. The under-predictions which occurred with ring removal were believed a result of ignoring the presence of spinning modes which are known to damp more rapidly in cylindrical ducts than would be predicted by least attenuated mode or plane wave analysis.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 76-541 , Aero-Acoustics Conference; Jul 20, 1976 - Jul 23, 1976; Palo Alto, CA
    Format: text
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  • 5
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    Noise reduction as affected by the extent and distribution of acoustic treatment in a turbofan engine inlet (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An inlet noise suppressor for a TF-34 engine designed to have three acoustically treated rings was tested with several different ring arrangements. The configurations included: all three rings; two outer rings; single outer ring; single intermediate ring, and finally no rings. It was expected that as rings were removed, the acoustic performance would be degraded considerably. While a degradation occurred, it was not as large as predictions indicated. The prediction showed good agreement with the data only for the full-ring inlet configuration. The underpredictions which occurred with ring removal were believed a result of ignoring the presence of spinning modes which are known to damp more rapidly in cylindrical ducts than would be predicted by least attenuated mode or plane wave analysis.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71904 , E-8693 , Aero-Acoustics Conf.; Jul 20, 1976 - Jul 22, 1976; Palo Alto, CA; United States
    Format: application/pdf
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  • 6
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    Analyses of ACPL thermal/fluid conditioning system (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of engineering analyses are reported. Initial computations were made using a modified control transfer function where the systems performance was characterized parametrically using an analytical model. The analytical model was revised to represent the latest expansion chamber fluid manifold design, and systems performance predictions were made. Parameters which were independently varied in these computations are listed. Systems predictions which were used to characterize performance are primarily transient computer plots comparing the deviation between average chamber temperature and the chamber temperature requirement. Additional computer plots were prepared. Results of parametric computations with the latest fluid manifold design are included.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-150065
    Format: application/pdf
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  • 7
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    A method to account for variation of average compressor inlet pressure during instantaneous distortion analyses (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method is presented to calculate the available surge margin as a function of time and incorporate it into an instantaneous distortion analysis. Results show that inlet pressure variations which cause only a small change at the compressor exit can cause a significant variation in the available surge margin.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-73438 , E-8793 , Propulsion Conf.; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA; United States
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  • 8
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    The influence of upstream conditions on flow reattachment lengths downstream of an abrupt circular channel expansion (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Biomechanics; 9; 1976
    Format: text
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  • 9
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    Re-examination of compliant wall experiments in air with water substrates (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A possible alternative explanation is proposed for compliant wall drag reductions measured in previous investigations. Standing waves were observed to form on the surfaces of compliant wall models in air with water substrates as the freestream velocity was increased from 15 to 30 m/s. These waves resembled sine waves with half of the wave protruding over the upstream portion of the model and the other half being recessed over the downstream end of the model. These data coupled with results of recent drag reduction experiments suggest that standing waves could have caused a shift in the model center of gravity creating a bending moment that was interpreted as a reduction in the skin friction drag.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Spacecraft and Rockets; 13; Aug. 197
    Format: text
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  • 10
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    Fluid dynamic research at NASA-Ames Research Center related to transonic wind tunnel design and testing techniques (1976)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: Fluid dynamic research with the objective of developing new and improved technology in both test facility concepts and test techniques is being reported. A summary of efforts and results thus far obtained in four areas is presented. The four area are: (1) the use of heavy gases to obtain high Reynolds numbers at transonic speeds: (2) high Reynolds number tests of the C-141A wing configuration; (3) performance and flow quality of the pilot injector driven wind tunnel; and (4) integration time required to extract accurate static and dynamic data from tests in transonic wind tunnels. Some of the principal conclusions relative to each of the four areas are: (1) Initial attempts to apply analytical corrections to test results using gases with gamma other than 1.4 to simulate conditions in air show promise but need significant improvement; (2) for the C-141A configuration, no Reynolds number less than the full scale flight value provides an accurate simulation of the full scale flow; (3) high ratios of tunnel mass flow rate to injection mass flow rate and high flow quality can be obtained in an injector driven transonic wind tunnel; and (4) integration times of 0.5 to 1.0 sec may be required for static force and pressure tests, respectively, at some transonic test conditions in order to obtain the required data accuracy.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD Wind Tunnel Design and Testing Tech.; 8 p
    Format: text
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