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  • 1
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    Status of advanced airfoil tests in the Langley 0.3-meter transonic cryogenic tunnel (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: A joint NASA/U.S. industry program to test advanced technology airfoils in the Langley 0.3-meter Transonic Tunnel (TCT) was formulated under the Langley ACEE Project Office. The objectives include providing U.S. industry an opportunity to compare their most advanced airfoils to the latest NASA designs by means of high Reynolds number tests in the same facility. At the same time, industry would again experience in the design and construction of cryogenic test techniques. The status and details of the test program are presented. Typical aerodynamic results obtained, to date, are presented at chord Reynolds number up to 45 x 10(6) and are compared to results from other facilities and theory. Details of a joint agreement between NASA and the Deutsche Forschungs- und Versuchsantalt fur Luft- and Raumfahrt e.V. (DFVLR) for tests of two airfoils are also included. Results of these tests will be made available as soon as practical.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advan. Aerodyn.: Selected NASA Res.; p 37-53
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Review of the advanced technology airfoil test program in the 0.3-meter transonic cryogenic tunnel (1984)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: The following areas were addressed: interchangeable test sections in the 0.3-M Transonic Cryogenic Tunnel (TCT); typical airfoil installation; airfoil capability; advanced technology airfoil test (ATAT); effects of the Reynolds number on the normal force coefficient; effects of the Reynolds number on the drag coefficient; and comparison of experimental results with theory.
    Schlagwort(e): AERODYNAMICS
    Materialart: Wind Tunnel Wall Interference Assessment and Correction, 1983; p 361-374
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 3
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    A new airfoil research capability (1979)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: The design and construction of a self streamlining wall test section for the Langley 0.3 meter transonic cryogenic tunnel was included in the fiscal year 1978 construction of facilities budget for Langley Research Center. The design is based on the research being carried out by M. J. Goodyer at the University of Southampton, Southampton, England, and is supported by Langley Research Center. This paper presents a brief description of the project. Included are some of the design considerations, anticipated operational envelope, and sketches showing the detail design concepts. Some details of the proposed operational mode, safety aspects, and preliminary schedule are presented.
    Schlagwort(e): AERODYNAMICS
    Materialart: Advanced Technol. Airfoil Res., Vol. 1, Pt. 1; p 425-432
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 4
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    Tests of a NACA 65(sub 1)-213 airfoil in the NASA Langley 0.3-meter transonic cryogenic tunnel (1984)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A wind-tunnel investigation was conducted to study the two dimensional aerodynamic characteristics of the NACA 65 sub 1-213 airfoil over a wide range of Reynolds numbers. Test temperature ranged from ambient to about 100K at pressures ranging from about 1.2 to 6.0 atm. Mach number was varied from 0.22 to 0.80 and Reynolds number (based on airfoil chord) from 3 million to 40 million. Data are included which demonstrate the effects of fixed transition, Mach number, and Reynolds number on the aerodynamic characteristics of the airfoil. A sample of data showing the effects of angle of attack on the pressure distribution is also given. The data are presented in an uncorrected form with no analysis.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-85732 , NAS 1.15:85732
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A fan pressure ratio correlation in terms of Mach number and Reynolds number for the Langley 0.3 meter transonic cryogenic tunnel (1980)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Calibration data for the two dimensional test section of the Langley 0.3 Meter Transonic Cryogenic Tunnel were used to develop a Mach number-Reynolds number correlation for the fan pressure ratio in terms of test section conditions. Well established engineering relationships combined to form an equation which is functionally analogous to the correlation. A geometric loss coefficient which is independent of Reynolds number or Mach number was determined. Present and anticipated uses of this concept include improvement of tunnel control schemes, comparison of efficiencies for operationally similar wind tunnels, prediction of tunnel test conditions and associated energy usage, and determination of Reynolds number scaling laws for similar fluid flow systems.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TP-1752 , L-13713
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 6
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    Description and calibration of the Langley 6- by 19-inch transonic tunnel (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A description and calibration is presented of the Langley 6- by 19-inch transonic tunnel which is a two-dimensional facility with top and bottom slotted walls used for testing two-dimensional airfoil sections. Basic tunnel-empty Mach number distributions and schlieren flow photographs as well as integrated normal-force coefficients, pitching-moment coefficients, surface-pressure distributions, and schlieren flow photographs of an NACA 0012 airfoil calibration model are presented. The Mach number capability of the facility is from 0.5 to about 1.1 with a corresponding Reynolds number range of 1.5 million to 3 million based on a 4.0-in. model chord. Comparisons of experimental results from the tests with previous data are also presented.
    Schlagwort(e): FACILITIES, RESEARCH, AND SUPPORT
    Materialart: NASA-TN-D-7182 , L-8680
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Description and calibration of the Langley 6- by 28-inch transonic tunnel (1975)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The Langley 6 by 28 inch transonic tunnel is described. The tunnel is a two dimensional facility with slotted top and bottom walls, used for testing two dimensional airfoil sections. Basic tunnel-empty Mach number distributions, noise surveys, and test section total pressure surveys are presented. The Mach number capability of the facility is from about 0.3 to 1.2. The stagnation pressure can be varied from 207 kN/sq m (30 lb/sq in) absolute to 620 kN/sq m (90 lb/sq in) absolute. This range of pressure can provide a Reynolds number of about 10 million, based on a 15.2 cm (6.0 in.) model chord at Mach numbers from 0.5 to 1.0. The maximum Reynolds number capability at a Mach number of 1.0 is about 15 million, based on the same model chord.
    Schlagwort(e): RESEARCH AND SUPPORT FACILITIES (AIR)
    Materialart: NASA-TN-D-8070 , L-10386
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Development of a computer program to obtain ordinates for NACA 4-digit, 4-digit modified, 5-digit, and 16 series airfoils (1975)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A computer program developed to calculate the ordinates and surface slopes of any thickness, symmetrical or cambered NACA airfoil of the 4-digit, 4-digit modified, 5-digit, and 16-series airfoil families is presented. The program produces plots of the airfoil nondimensional ordinates and a punch card output of ordinates in the input format of a readily available program for determining the pressure distributions of arbitrary airfoils in subsonic potential viscous flow.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-3284 , L-10375
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Development of a computer program to obtain ordinates for NACA-6 and 6A-series airfoils (1974)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A computer program was developed to produce the ordinates for airfoils of any thickness, thickness distribution, or camber in the NACA 6- and 6A-series. For the 6-series and for all but the leading edge of the 6A-series, agreement between the ordinates obtained from the new program and previously published values is generally within .00005 chord. Near the leading edge of the 6A-series airfoils, differences up to .00035 chord are found.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-3069 , L-9558
    Format: application/pdf
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  • 10
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    Hypersonic aerodynamic characteristics of DL-4 lifting entry vehicle (1970)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Analysis of aerodynamic forces on DL-4 lifting entry vehicle and comparison with theoretical methods
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-1994 , L-6592
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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