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  • Organic Chemistry  (20)
  • AERODYNAMICS  (16)
  • 1990-1994  (14)
  • 1985-1989  (22)
  • 1
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    Real gas effects on the numerical simulation of a hypersonic inlet (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The present use of a parabolized Navier-Stokes solver to accurately simulate the flowfield in a supersonic inlet yields good agreement between numerical analysis and experiment for a Mach 7.4 inlet under cruise conditions, with an internal compression ratio of 8. The significance of real gas effects on the performance calculation of a hypersonic inlet is demonstrated, with small changes in the ratio of specific heats resulting in a substantial change in the calculated pitot pressure ratio.
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 2; 381
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Further buffeting tests in a cryogenic wind tunnel (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Further measurements of buffeting, using wing-root strain gauges, were made in the NASA Langley 0.3 m Cryogenic Wind Tunnel to refine techniques which will be used in larger cryogenic facilities such as the United States National Transonic Facility (NTF) and European Transonic Wind Tunnel (ETW). The questions addressed included the relative importance of variations in frequency parameter and Reynolds number, the choice of model material (considering both stiffness and damping) and the effects of static aeroelastic distortion. The main series of tests was made on half models of slender 65 deg delta wings with a sharp leading edge. The three delta wings had the same planform but widely different bending stiffness and frequencies (obtained by varying both the material and the thickness of the wings). It was known that the flow on this configuration would be insensitive to variations in Reynold number. Additional tests were made on one unswept half-wing of aspect ratio 1.5 with an NPL 9510 aerofoil section, known to be sensitive to variations in Reynolds number at transonic speeds. For brevity the test Mach numbers were restricted to M = 0.21 and 0.35 for the delta wings and to M = 0.30 for the unswept wing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-107621 , NAS 1.15:107621 , RAE-TM-AERO-2231
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Application of a computational model for vortex generators in subsonic internal flows (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A model for the analysis of vortex generators in a fully viscous subsonic internal flow is evaluated. A vorticity source term is used in a modified form of the Parabolized Navier-Stokes equations to model the shed vortex. Computed results are compared with idealized flow vortex paths, and with experimental data for vortex generators embedded in a thick turbulent boundary layer. The analysis is also compared with experimental data for a separated diffusing S-duct and for a diffusing S-duct with vortex generators. Quantitative comparisons are shown for the latter three cases. Emphasis is placed on verifying the ability of the model to predict global distortions in the flow field.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-1458
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Pressure distributions from high Reynolds number tests of a Boeing BAC 1 airfoil in the Langley 0.3-meter transonic cryogenic tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind-tunnel investigation designed to test a Boeing advanced-technology airfoil from low to flight-equivalent Reynolds numbers has been completed in the Langley 0.3-Meter Transonic Cryogenic Tunnel. This investigation represents the first in a series of NASA/U.S. industry two-dimensional airfoil studies to be completed in the Advanced Technology Airfoil Test program. Test temperature was varied from ambient to about 100 K at pressures ranging from about 1.2 to 6.0 atm. Mach number was varied from about 0.40 to 0.80. These variables provided a Reynolds number (based on airfoil chord) range from 4.4 X 10 to the 6th power to 50.0 X 10 to the 6th power. All the test objectives were met. The pressure data are presented without analysis in plotted and tabulated formats for use in conjunction with the aerodynamic coefficient data published as NASA TM-81922. At the time of the test, these pressure data were considered proprietary and have only recently been made available by Boeing for general release. Data are included which demonstrate the effects of fixed transition. Also included are remarks on the model design, the model structural integrity, and the overall test experience.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87600 , L-16010 , NAS 1.15:87600
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Pressure distribution from high Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-meter transonic cryogenic tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation of a NASA 12-percent-thick, advanced-technology supercritical airfoil was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT). This investigation represents another in the series of NASA/U.S. industry two-dimensional airfoil studies to be completed in the Advanced Technology Airfoil Tests program. Test temperature was varied from 220 K to 96 K at pressures ranging from 1.2 to 4.3 atm. Mach number was varied from 0.50 to 0.80. This investigation was designed to: (1) test a NASA advanced-technology airfoil from low to flight equivalent Reynolds numbers, (2) provide experience in cryogenic wind-tunnel model design and testing techniques, and (3) demonstrate the suitability of the 0.3-m TCT as an airfoil test facility. All the test objectives were met. The pressure data are presented without analysis in tabulated format and as plots of pressure coefficient versus position on the airfoil. This report was prepared for use in conjunction with the aerodynamic coefficient data published in NASA-TM-86371. Data are included which demonstrate the effects of fixed transition. Also included are remarks on the model design and fabrication.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86370 , L-15908 , NAS 1.15:86370
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    High Reynolds number tests of a NASA SC(3)-0712(B) airfoil in the Langley 0.3-meter transonic cryogenic tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation of a NASA 12-percent-thick, advanced-technology supercritical airfoil was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (TCT). This investigation represents another in the series of NASA/U.S. industry two-dimensional airfoil studies to be completed in the Advanced Technology Airfoil Tests program. Test temperature was varied from 220 K to 96 K at pressures ranging from 1.2 to 4.3 atm. Mach number was varied from 0.60 to 0.80. These variables provided a Reynolds number range from 4,400,000 to 40,000,000 based on a 15.24-cm (6.0-in.) airfoil chord. This investigation was designed to test a NASA advanced-technology airfoil from low to flight-equivalent Reynolds numbers, provide experience in cryogenic wind tunnel model design and testing techniques, and demonstrate the suitability of the 0.3-m TCT as an airfoil test facility. The aerodynamic results are presented as integrated force and moment coefficients and pressure distributions. Data are included which demonstrate the effects of fixed transition, Mach number, and Reynolds number on the aerodynamic characteristics. Also included are remarks on the model design, the model structural integrity, and the overall test experience.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86371 , L-15909 , NAS 1.15:86371
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Analytical modeling of circuit aerodynamics in the new NASA Lewis Altitude Wind Tunnel (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Rehabilitation and extention of the capability of the altitude wind tunnel (AWT) was analyzed. The analytical modelling program involves the use of advanced axisymmetric and three dimensional viscous analyses to compute the flow through the various AWT components. Results for the analytical modelling of the high speed leg aerodynamics are presented; these include: an evaluation of the flow quality at the entrance to the test section, an investigation of the effects of test section bleed for different model blockages, and an examination of three dimensional effects in the diffuser due to reentry flow and due to the change in cross sectional shape of the exhaust scoop.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0380
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Dynamic ground effects on a two-dimensional flat plate (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effect of time-variant vortex shedding is simulated by a sequence of discrete vortices convecting downstream in the wake of a two-dimensional flat plate whose lifting condition is modeled by means of the quasi-vortex lattice method. The boundary condition of this problem is specified in such a way that the tangency condition on the surface of the flat plate is satisfied; the boundary condition also takes into account the effect of airfoil motion relative to the ground. Significant lift changes are shown to occur, due to the dynamic ground effect, that are crucial in aircraft takeoff and landing transitions.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 638-640
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Aerodynamic instability performance of an advanced high-pressure-ratio compression component (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The data acquisition and reduction, test procedures, and results of in-stall and in-surge testing of a NASA high-pressure-ratio compression component are discussed, in addition to the compressor-rig configuration and instrumentation used. Data analysis revealed information about rotating stall hysteresis, rotating stall development and cessation times, and rotating-stall-cell flow blockage. It is found that hysteresis exists in the work coefficient as well as in the pressure coefficient. Airflow rakes were designed to study the in-surge transient response of the compressor. The quasi-steady compressor characteristics underlying the transient-surge data were investigated using a parameter-identification technique.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-1619
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    A summary of Reynolds number effects on some recent tests in the Langley 0.3-meter transonic cryogenic tunnel (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Reynolds number effects noted from selected test programs conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (0.3-m TCT) are discussed. The tests, which cover a unit Reynolds number range from about 2.0 to 80.0 million per foot, summarize effects of Reynolds number on: (1) aerodynamic data from a supercritical airfoil, (2) results from several wall interference correction techniques, and (3) results obtained from advanced, cryogenic tests techniques. The test techniques include: (1) use of a cryogenic sidewall boundary layer removal system, (2) detailed pressure and hot wire measurements to determine test section flow quality, and (3) use of a new hot film system suitable for transition detection in a cryogenic wind tunnel. The results indicate that Reynolds number effects appear most significant when boundary layer transition effects are present and at high lift conditions when boundary layer separation exists on both the model and the tunnel sidewall.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 861765
    Format: text
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    NASA TECHNICAL REPORTS
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