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  • AERODYNAMICS  (383)
  • Fisheries
  • 2020-2023
  • 2010-2014
  • 1975-1979  (384)
  • 1950-1954
  • 1977  (384)
  • 1
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    Turbulence modeling of shock separated boundary-layer flows (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Computations of transonic and hypersonic shock-separated boundary-layer flows using zero-equation (algebraic), one-equation (kinetic energy), and two-equation (kinetic energy plus length scale) turbulence eddy viscosity models are described and compared with measurements. The computations make use of a new Navier-Stokes computer algorithm that has reduced computing times by one to two orders of magnitude. The algorithm, and how the turbulence models are incorporated into it, are described. Results for the transonic flow show that the unmodified one-equation model is superior to the zero-equation model in skin-friction predictions. For the hypersonic flow, a highly modified one-equation model that accurately predicts surface pressure and heat transfer is described. Preliminary two-equation model results are also presented.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulent Shear Flows; Apr 18, 1977 - Apr 20, 1977; University Park, PA
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Computation of unsteady transonic flows by the indicial method (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The indicial method is investigated for the computation of unsteady transonic force and moment coefficients for use in flutter analyses. This approach has the advantage that solutions for all reduced frequencies for a given mode of motion can be obtained from a single finite-difference flowfield computation. Comparisons of indicial and time-integration computations for oscillating airfoil and flap motions help define limits on the motion amplitude for the applicability of the indicial method to transonic flows. Within these limits, solutions for various motion modes can be superposed to obtain solutions for multiple-degree-of-freedom aeroelastic systems. Also, a simple aeroelastic problem is solved by an alternative approach in which the structural motion and flowfield equations are integrated simultaneously using a time-integration finite-difference procedure.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 77-447 , Mar 24, 1977 - Mar 25, 1977|Conference on Structures, Structural Dynamics and Materials; Mar 21, 1977 - Mar 23, 1977; San Diego, CA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flutter analysis of a glider made of synthetic materials (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A description of the flutter behavior of the Standard Cirrus is given. Steady vibration tests were conducted, and vibration and flutter calculations were made.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75160
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A survey of computational aerodynamics in the United States (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Programs in theoretical and computational aerodynamics in the United States are described. Those aspects of programs that relate to aeronautics are detailed. The role of analysis at various levels of sophistication is discussed as well as the inverse solution techniques that are of primary importance in design methodology. The research is divided into the broad categories of application for boundary layer flow, Navier-Stokes turbulence modeling, internal flows, two-dimensional configurations, subsonic and supersonic aircraft, transonic aircraft, and the space shuttle. A survey of representative work in each area is presented.
    Keywords: AERODYNAMICS
    Type: NASA-SP-394
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Wake Vortex Minimization (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A status report is presented on research directed at reducing the vortex disturbances of aircraft wakes. The objective of such a reduction is to minimize the hazard to smaller aircraft that might encounter these wakes. Inviscid modeling was used to study trailing vortices and viscous effects were investigated. Laser velocimeters were utilized in the measurement of aircraft wakes. Flight and wind tunnel tests were performed on scale and full model scale aircraft of various design. Parameters investigated included the effect of wing span, wing flaps, spoilers, splines and engine thrust on vortex attenuation. Results indicate that vortives may be alleviated through aerodynamic means.
    Keywords: AERODYNAMICS
    Type: NASA-SP-409 , Feb 25, 1976 - Feb 26, 1976; Washington
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Aerodynamic Characteristics at Mach Numbers from 0.6 to 2.16 of a Supersonic Cruise Fighter Configuration with a Design Mach Number of 1.8 (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An investigation was made in the Langley 8-foot transonic tunnel and the Langley Unitary Plan wind tunnel, over a Mach number range of 0.6 to 2.16, to determine the static longitudinal and lateral aerodynamic characteristics of a model of a supersonic-cruise fighter. The configuration, which is designed for efficient cruise at Mach number 1.8, is a twin-engine tailless arrow-wing concept with a single rectangular inlet beneath the fuselage and outboard vertical tails and ventral fins. It had untrimmed values of lift-drage ratio ranging from 10 at subsonic speeds to 6.4 at the design Mach number. The configuration was statically stable both longitudinally and laterally.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3559 , L-11604
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Investigation of Inlet Concepts for Maneuver Improvement at Transonic Speeds (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A 15 percent scale lightweight fighter type inlet forebody was tested in the Ames 14 foot transonic wind tunnel at Mach numbers of 0.7, 0.9, and 1.04. The inlet was a two dimensional horizontal ramp system designed for a Mach number of 2.2. Four inlet devices designed to prevent or delay cowl-lip boundary layer separation or to improve the inlet internal flow characteristics at high angles of attack were investigated. The devices used to control cowl-lip separation consisted of cowl leading edge flaps, slotted flaps, and tangential blowing. To improve the internal flow characteristics, discrete jet nozzle flows were directed downstream and parallel to the duct surface in the subsonic diffuser to energize the wall boundary layer. The discrete jets used in the subsonic diffuser were also tested in combination with each of the cowl leading edge devices. Test measurements included engine-face total pressure recovery, steady state distortion, dynamic distortion, duct boundary layer profiles, and duct-surface static pressures.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-73215 , A-6952
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Instability of a compressible circular free jet with consideration of the influence of the jet boundary layer thickness (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The instability of a circular jet was investigated by means of the inviscid linearized stability theory. By variation of a jet parameter which takes the ratio of jet radius to boundary layer thickness into account, the influence of axisymmetry on the spatial growth rate and disturbance phase velocity is studied. The influence of Mach number and temperature ratio is discussed. A comparison with measurements shows that the instability of a turbulent jet boundary layer may also be explained by these results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75190
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Effect of flap deflection on the lift coefficient of wings operating in a biplane configuration (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Biplane models with a lift flap were tested in a wind tunnel to study the effect of flap deflection on the aerodynamic coefficient of the biplane as well as of the individual wings. Optimization of the position flap was carried out, and the effect of changes in the chord length of the lower wing was determined for the aerodynamic structure of a biplane with a lift flap on the upper wing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75059
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Small disturbances in a compressor with strong swirl (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A detailed time resolved study of the flow field upstream and downstream of a high work transonic compressor rotor shows that the flow field is dominated by the downstream evolution of the viscous flow shed from the rotor blades under the influence of the strong mean swirl. The dominant periodicity in the flow changes from blade passing to 1.4 times blade passing within one chord from the blade row. A possible explanation is that the wakes evolve to a shear eigenmode of the swirling flow, as suggested by perturbation theory. Another possibility is a 'propagating stall' of 16 cells, but the rotor operated near its design point. Treatments of 'turbulence' in turbomachines should account for such phenomena, which originate in the strong mean swirl.
    Keywords: AERODYNAMICS
    Type: SQUID Workshop; 15, 1976; Warrenton, VA
    Format: text
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