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  • 1
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    Evolution of vortex structures over flapping foils in shear flows and its impact on aerodynamic performance (2018)
    Elsevier
    Details
    Publication Date: 2018-01-01
    Print ISSN: 0889-9746
    Electronic ISSN: 1095-8622
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    The effects of streamline curvature and swirl on turbulent flows in curved ducts (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique for improving the numerical predictions of turbulent flows with the effect of streamline curvature is developed. Separated flows, the flow in a curved duct, and swirling flows are examples of flow fields where streamline curvature plays a dominant role. A comprehensive literature review on the effect of streamline curvature was conducted. New algebraic formulations for the eddy viscosity incorporating the kappa-epsilon turbulence model are proposed to account for various effects of streamline curvature. The loci of flow reversal of the separated flows over various backward-facing steps are employed to test the capability of the proposed turbulence model in capturing the effect of local curvature. The inclusion of the effect of longitudinal curvature in the proposed turbulence model is validated by predicting the distributions of the static pressure coefficients in an S-bend duct and in 180 degree turn-around ducts. The proposed turbulence model embedded with transverse curvature modification is substantiated by predicting the decay of the axial velocities in the confined swirling flows. The numerical predictions of different curvature effects by the proposed turbulence models are also reported.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-187759 , NAS 1.26:187759 , KU-FRL-793-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Turbulent swirling jets with excitation (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An existing cold-jet facility at NASA Lewis Research Center was modified to produce swirling flows with controllable initial tangential velocity distribution. Two extreme swirl profiles, i.e., one with solid-body rotation and the other predominated by a free-vortex distribution, were produced at identical swirl number of 0.48. Mean centerline velocity decay characteristics of the solid-body rotation jet flow exhibited classical decay features of a swirling jet with S - 0.48 reported in the literature. However, the predominantly free-vortex distribution case was on the verge of vortex breakdown, a phenomenon associated with the rotating flows of significantly higher swirl numbers, i.e., S sub crit greater than or equal to 0.06. This remarkable result leads to the conclusion that the integrated swirl effect, reflected in the swirl number, is inadequate in describing the mean swirling jet behavior in the near field. The relative size (i.e., diameter) of the vortex core emerging from the nozzle and the corresponding tangential velocity distribution are also controlling factors. Excitability of swirling jets is also investigated by exciting a flow with a swirl number of 0.35 by plane acoustic waves at a constant sound pressure level and at various frequencies. It is observed that the cold swirling jet is excitable by plane waves, and that the instability waves grow about 50 percent less in peak r.m.s. amplitude and saturate further upstream compared to corresponding waves in a jet without swirl having the same axial mass flux. The preferred Strouhal number based on the mass-averaged axial velocity and nozzle exit diameter for both swirling and nonswirling flows is 0.4.
    Keywords: AERODYNAMICS
    Type: NASA-CR-180895 , NAS 1.26:180895
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Spectral analysis of unsteady surface pressure on a pusher propeller (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A propeller of an advanced turboprop testbed aircraft in pusher configuration is instrumented with 22 miniature blade-mounted transducers (BMTs) at two radii. Upstream pylon wake interaction with the propeller is the source of a one-per-cycle excitation for the blades in flight. The time history of fluctuating pressure signals over 26 flight conditions is statistically analyzed in the frequency domain. The rms amplitude of fluctuating pressure signals measured by suction surface BMTs indicates a very strong presence of the fundamental frequency over most of the upper surface. The pylon wake pressure signature on the propeller trailing edge, i.e., x/c not less than 0.80, shows predominantly random turbulence; hence, the amplitude of the fundamental frequency wave is fairly small. The resurgence of a large amplitude fundamental harmonic with coherent pylon wake signature further downstream, say at 90 percent chord, is unexpected behavior. The appearance of a dominating second propeller shaft order in the spectra of the rms pressure in transonic flight conditions identifies the presence of a two-per-cycle excitation source in the azimuthal direction. This is due to the presence of a shock wave, as evidenced by the pressure-time history plots.
    Keywords: AERODYNAMICS
    Type: In: Rotating machinery - Transport phenomena; Proceedings of the 3rd International Symposium on Transport Phenomena and Dynamics of Rotating Machinery (ISROMAC-3), Honolulu, HI, Apr. 1-4, 1990 (A93-54; p. 665-680.
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Pressure-time history of pylon wake signature on a pusher propeller in flight (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Miniature, high-frequency, pressure transducers were mounted on a pusher propeller at 3/4 and 90-percent radii. Time-history of fluctuating surface pressure over 700 revolutions and 26 flight conditions reveal intriguing phenomena. The anticipated pylon wake signature manifests itself as a negative pressure pulse over extended portions of the suction surface. The phenomenon further develops into a primarily random turbulence signature at 80-percent chord and interestingly may reevolve as a coherent wake signature further downstream. A new type of periodic disturbance of long time-scale, compared to propeller period-of-revolution, is discovered at positions beyond 0.6 chord on the suction surface in the transonic regime.
    Keywords: ACOUSTICS
    Type: AIAA PAPER 89-2052
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    A study of three dimensional turbulent boundary layer separation and vortex flow control using the reduced Navier Stokes equations (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A reduced Navier-Stokes (RNS) initial value space marching solution technique was applied to vortex generator and separated flow problems and demonstrated good predictions of the engine face flow field. This RNS solution technique using FLARE approximations can adequately describe the topological and topographical structure flow separation associated with vortex liftoff, and this conclusion led to the concept of a subclass of separations which can be called vorticity separations: separations dominated by the transport of vorticity. Adequate near wall resolution of vorticity separations appears necessary for good predictions of these flows.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulent Shear Flows; Sept. 9-11, 1991; Munich; Germany
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Modern developments in shear flow control with swirl (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Passive and active control of swirling turbulent jets is experimentally investigated. Initial swirl distribution is shown to dominate the free jet evolution in the passive mode. Vortex breakdown, a manifestation of high intensity swirl, was achieved at below critical swirl number (S = 0.48) by reducing the vortex core diameter. The response of a swirling turbulent jet to single frequency, plane wave acoustic excitation was shown to depend strongly on the swirl number, excitation Strouhal number, amplitude of the excitation wave, and core turbulence in a low speed cold jet. A 10 percent reduction of the mean centerline velocity at x/D = 9.0 (and a corresponding increase in the shear layer momentum thickness) was achieved by large amplitude internal plane wave acoustic excitation. Helical instability waves of negative azimuthal wave numbers exhibit larger amplification rates than the plane waves in swirling free jets, according to hydrodynamic stability theory. Consequently, an active swirling shear layer control is proposed to include the generation of helical instability waves of arbitrary helicity and the promotion of modal interaction, through multifrequency forcing.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-186586 , NAS 1.26:186586 , KU-FRL-724-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    On the aerodynamics and performance of active vortex generators (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: As a building block in the development of smart lift-enhancement devices, a new concept for flow control using active vortex generators (AVGs) is presented. Ramp, wedge, and doublet wedge (Wheeler) VG configurations are investigated. The AVGs are designed to conform to the surface of the wing section at low alpha. As the section approaches the stall, they are deployed and accordingly, alpha(stall) and C(lmax) are increased. A qualitative analysis of the flow around the various VG configurations was conducted in a low speed wind tunnel at 1.6 ft/s and a Reynolds number of approximately 3400. The results demonstrate that ramp VGs produce vortices that have the longest distance at breakdown. The VGs were also applied to a 25-in. span, 8-in. chord NACA 4415 wing section. Optimization studies were conducted on the spanwise spacing, chordwise position, and size of statically deployed VGs. The test results demonstrate a 14-percent increase in C(lmax) while increasing alpha (stall) by up to 3.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3447 , In: AIAA Applied Aerodynamics Conference, 11th, Monterey, CA, Aug. 9-11, 1993, Technical Papers. Pt. 1 (A93-47201 19-02); p. 376-386.
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A study of three dimensional turbulent boundary layer separation and vortex flow control using the reduced Navier Stokes equations (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A reduced Navier Stokes (RNS) initial value space marching solution technique was applied to vortex generator and separated flow problems and demonstrated good predictions of the engine face flow field. This RNS solution technique using FLARE approximations can adequately describe the topological and topographical structure flow separation associated with vortex liftoff, and this conclusion led to the concept of a subclass of separations which can be called vorticity separations: separations dominated by the transport of vorticity. Adequate near wall resolution of vorticity separations appears necessary for good predictions of these flows.
    Keywords: AERODYNAMICS
    Type: NASA-TM-104407 , E-6233 , NAS 1.15:104407 , Turbulent Shear Flow Symposium; Sep 09, 1991 - Sep 11, 1991; Munich; Germany
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Pressure-time history of pylon wake on a pusher propeller in flight (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: ACOUSTICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 6; 758-768
    Format: text
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    NASA TECHNICAL REPORTS
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