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  • 1
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    Recent results on the aerodynamics of winged missiles (1966)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Aircraft Aerodynamics; p 485-495
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Operational flow visualization techniques in the Langley Unitary Plan Wind Tunnel (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The unitary plan wind tunnel (UPWT) uses in daily operation are shown. New ideas for improving the quality of established flow visualization methods are developed and programs on promising new flow visualization techniques are pursued. The unitary plan wind tunnel is a supersonic facility, referred to as a production facility, although the majority of tests are inhouse basic research investigations. The facility has two 4 ft. by 4 ft. test sections which span a Mach range from 1.5 to 4.6. The cost of operation is about $10 per minute. Problems are the time required for a flow visualization test setup and investigation costs and the ability to obtain consistently repeatable results. Examples of sublimation, vapor screen, oil flow, minitufts, schlieren, and shadowgraphs taken in UPWT are presented. All tests in UPWT employ one or more of the flow visualization techniques.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Flow Visualization and Laser Velocimetry for Wind Tunnels; p 65-73
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Supersonic aerodynamic characteristics of a series of related bodies with cross-sectional ellipticity (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Supersonic aerodynamic characteristics of series of lifting bodies with cross-sectional ellipticity
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3539
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Vapor-screen technique for flow visualization in the Langley Unitary Plan Wind Tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The vapor-screen technique for flow visualization, as developed for the Langley Unitary Plan Wind Tunnel, is described with evaluations of light sources and photographic equipment. Test parameters including dew point, pressure, and temperature were varied to determine optimum conditions for obtaining high-quality vapor-screen photographs. The investigation was conducted in the supersonic speed range for Mach numbers from 1.47 to 4.63 at model angles of attack up to 35 deg. Vapor-screen photographs illustrating various flow patterns are presented for several missile and aircraft configurations. Examples of vapor-screen results that have contributed to the understanding of complex flow fields and provided a basis for the development of theoretical codes are presented with reference to other research.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86384 , L-15902 , NAS 1.15:86384
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Surface pressure data for a supersonic-cruise airplane configuration at Mach numbers of 2.30, 2.96, 3.30 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The tabulated results of surface pressure tests conducted on the wing and fuselage of an airplane model in the Langley Unitary Plan wind tunnel are presented without analysis. The model tested was that of a supersonic-cruise airplane with a highly swept arrow-wing planform, two engine nacelles mounted beneath the wing, and outboard vertical tails. Data were obtained at Mach numbers of 2.30, 2.96, and 3.30 for angles of attack from -4 deg to 12 deg. The Reynolds number for these tests was 6,560,000 per meter.
    Keywords: AERODYNAMICS
    Type: NASA-TM-80061 , L-12777
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Development of a metric half-span model for interference free testing (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A metric half-span model has been developed which allows measurement of aerodynamic forces and moments without support interference or model distortion. This is accomplished by combining the best features of the conventional sting/balance and half-span splitter plate supports, For example, forces and moments are measured on one-half of a symmetrical model which is mechanically supported by a sting on the nonmetric half. Tests were performed in the Langley Unitary Plan wind tunnel over a Mach range of 1.60 to 2.70 and an angle-of-attack range of 04 deg to 20 deg. Preliminary results on concept evaluation, and effect of fuselage modification to house a conventional balance and sting are presented.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 80-0460 , Aerodynamics Testing Conference; Mar 18, 1980 - Mar 20, 1980; Colorado Springs, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Description and calibration of the Langley unitary plan wind tunnel (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The two test sections of the Langley Unitary Plan Wind Tunnel were calibrated over the operating Mach number range from 1.47 to 4.63. The results of the calibration are presented along with a a description of the facility and its operational capability. The calibrations include Mach number and flow angularity distributions in both test sections at selected Mach numbers and tunnel stagnation pressures. Calibration data are also presented on turbulence, test-section boundary layer characteristics, moisture effects, blockage, and stagnation-temperature distributions. The facility is described in detail including dimensions and capacities where appropriate, and example of special test capabilities are presented. The operating parameters are fully defined and the power consumption characteristics are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1905 , L-14024
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Test technique development in interference free testing, flow visualization, and remote control model technology at Langley's Unitary Plan wind tunnel (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A metric half-span model is considered as a means of mechanical support for a wind-tunnel model which allows measurement of aerodynamic forces and moments without support interference or model distortion. This technique can be applied to interference-free propulsion models. The vapor screen method of flow visualization at supersonic Mach numbers is discussed. The use of smoke instead of water vapor as a medium to produce the screen is outlined. Vapor screen data are being used in the development of analytical vortex tracking programs. Test results for a remote control model system are evaluated. Detailed control effectiveness and cross-coupling data were obtained with a single run. For the afterbody tail configuration, tested control boundaries at several roll orientations were established utilizing the facility's on-line capability to 'fly' the model in the wind tunnel.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Supersonic Tunnel Association, Semi-Annual Meeting, 52nd, Notre Dame; Sept. 13-14, 1979; Notre Dame, Ind
    Format: text
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    NASA TECHNICAL REPORTS
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