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  • AERODYNAMICS  (99)
  • GENERAL
  • 1975-1979  (101)
  • 1955-1959
  • 1979  (101)
  • 1
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    On turbulence modeling for unsteady transonic flows (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A detailed examination of the turbulent field in an unsteady transonic flow undergoing shock-induced separation is conducted. Ensemble-averaged mean and fluctuating velocities, obtained from conditionally sampled laser velocimeter data, are described and analyzed to assess the applicability of modeling concepts usually employed in steady-flow problems. Some comparisons with computations employing the Reynolds averaged Navier-Stokes equations with a mixing length turbulence model are then presented to illustrate the status of current predictive capabilities. The results appear to imply that turbulence models developed for steady flows apply and that the model need not reflect all the fine details of the turbulent structure but rather account in an approximate way for the production and destruction of the turbulence.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0071 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Pitot pressure measurements in flow fields behind circular-arc nozzles with exhaust jets at subsonic free-stream Mach numbers (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The flow field behind a circular arc nozzle with exhaust jet was studied at subsonic free stream Mach numbers. A conical probe was used to measure the pitot pressure in the jet and free stream regions. Pressure data were recorded for two nozzle configurations at nozzle pressure ratios of 2.0, 2.9, and 5.0. At each set of test conditions, the probe was traversed from the jet center line into the free stream region at seven data acquisition stations. The survey began at the nozzle exit and extended downstream at intervals. The pitot pressure data may be applied to the evaluation of computational flow field models, as illustrated by a comparison of the flow field data with results of inviscid jet plume theory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-80169 , L-13060
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Bumblebee program: Aerodynamic data. Part 3: Pressure fields at Mach numbers 1.5 and 2.0 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A large amount of fundamental aerodynamic missile data, which were stored for a number of years at the Applied Physics Laboratory, are reported. Data that supplements the M = 2.0 flow field data are provided. The Mach number effect by means of pressure fields only, at M = 1.5 and 2.0, and at angles of attack up to 23 deg at a mid-body station where a wing might be located is described.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3116
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Bumblebee program, aerodynamic data. Part 2: Flow fields at Mach number 2.0 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Available flow field data which can be used in validating theoretical procedures for computing flow fields around supersonic missiles are presented. Tabulated test data are given which define the flow field around a conical-nosed cylindrical body in a crossflow plane corresponding to a likely tail location. The data were obtained at a Mach number of 2.0 for an angle of attack of 0 to 23 degrees. The data define the flow field for cases both with and without a forward wing present.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3115
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Advanced missile technology. A review of technology improvement areas for cruise missiles (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technology assessments in the areas of aerodynamics, propulsion, and structures and materials for cruise missile systems are discussed. The cruise missiles considered cover the full speed, altitude, and target range. The penetrativity, range, and maneuverability of the cruise missiles are examined and evaluated for performance improvements.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3187 , BFD-0-79-001
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flight-measured afterbody pressure coefficients from an airplane having twin side-by-side jet engines for Mach numbers from 0.6 to 1.6 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Afterbody pressure distribution data were obtained in flight from an airplane having twin side-by-side jet exhausts. The data were obtained in level flight at Mach numbers from 0.60 to 1.60 and at elevated load factors for Mach numbers of 0.60, 0.90, and 1.20. The test altitude varied from 2300 meters (7500 feet) to 15,200 meters (50,000 feet) over a speed range that provided a matrix of constant Mach number and constant unit Reynolds number test conditions. The results of the full-scale flight afterbody pressure distribution program are presented in the form of plotted pressure distributions and tabulated pressure coefficients with Mach number, angle of attack, engine nozzle pressure ratio, and unit Reynolds number as controlled parameters.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1549 , H-1066
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Bumblebee Program: Aerodynamic data. Part 4: Wing loads at Mach numbers 1.5 and 2.0 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Individual wing panel aerodynamic characteristics are provided for rectangular wings with aspect ratios of 0.25, 0.75, and 1.00 each panel at Mach numbers if 1.5 and 2.0 for angles of attack to 23 degrees. Data plots produced from reports of wind tunnel tests show normal force coefficients, and the spanwise and chordwise center of pressure locations.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3117
    Format: application/pdf
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  • 8
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    Bumblebee program. Aerodynamic data. Part 1: Supersonic flow field, pressure field, and panel load data for validation of computational methods (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The parts of an aerodynamics research project of the Bumblebee Program, called Generalized Missile study, is described. The source related, and potential applications are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3114
    Format: application/pdf
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  • 9
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    Implicit finite-difference simulations of steady and unsteady transonic flows (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Implicit methods for several fluid dynamic formulations have been developed and applied to steady-state and low-frequency transonic flows. The basic steps involved in the construction of implicit schemes include: selection of linearly stable accurate implicit difference operators, time-linearization of nonlinear terms, and approximate factorization of the implicit operators into easily solved systems of equations. The proposed schemes are found very efficient for the simpler formulations.
    Keywords: AERODYNAMICS
    Type: International Conference on Numerical Methods in Fluid Dynamics; Jun 21, 1978 - Jun 24, 1978; Tiflis; Georgian
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Numerical simulation of steady supersonic viscous flow (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A noniterative, implicit, space-marching, finite-difference algorithm is developed for the steady thin-layer Navier-Stokes equations in conservation-law-form. The numerical algorithm is applicable to steady supersonic viscous flow over bodies of arbitrary shape. In addition, the same code can be used to compute supersonic inviscid flow or three-dimensional boundary layers. Computed results from two-dimensional and three-dimensional versions of the numerical algorithm are in good agreement with those obtained from more costly time-marching techniques.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0130 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
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