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  • 1
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    Energy management and recovery (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Energy management is treated by first exploring the energy requirements for a cryogenic tunnel. The requirement is defined as a function of Mach number, Reynolds number, temperature, and tunnel size. A simple program and correlation is described which allow calculation of the energy required. Usage of energy is also addressed in terms of tunnel control and research operation. The potential of a new wet expander is outlined in terms of cost saved by reliquefying a portion of the exhaust. The expander is described as a potentially more efficient way of recovering a fraction of the cold nitrogen gas normally exhausted to the atmosphere from a cryogenic tunnel. The role of tunnel insulation systems is explored in terms of requirements, safety, cost, maintenance, and efficiency. A detailed description of two external insulation systems is given. One is a rigid foam with a fiber glass and epoxy shell. The other is composed of glass fiber mats with a flexible outer vapor barrier; this system is nitrogen purged. The two systems are compared with the purged system being judged superior.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD, Special Course on Advances in Cryogenic Wind Tunnel Technology; 9 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Models for cryogenic wind tunnels (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Model requirements, types of model construction methods, and research in new ways to build models are discussed. The 0.3-m Transonic Cryogenic Tunnel was in operation for 16 years and many 2-D airfoil pressure models were tested. In addition there were airfoil models dedicated to transition detection techniques and other specialized research. There were also a number of small 3-D models tested. A chronological development in model building technique is described which led to the construction of many successful models. The difficulties of construction are illustrated by discussing several unsuccessful model fabrication attempts. The National Transonic Facility, a newer and much larger tunnel, was used to test a variety of models including a submarine, transport and fighter configurations, and the Shuttle Orbiter. A new method of building pressure models was developed and is described. The method is centered on the concept of bonding together plates with pressure channels etched into the bond planes, which provides high density pressure instrumentation with minimum demand on parent model material. With care in the choice of materials and technique, vacuum brazing can be used to produce strong bonds without blocking pressure channels and with no bonding voids between channels. Using multiple plates, a 5 percent wing with 96 orifices was constructed and tested in a transonic cryogenic wind tunnel. Samples of test data are presented and future applications of the technology are suggested.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD, Special Course on Advances in Cryogenic Wind Tunnel Technology; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Test techniques for cryogenic wind tunnels (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Some of the testing techniques developed for transonic cryogenic tunnels are presented. Techniques are emphasized which required special development or were unique because of the opportunities offered by cryogenic operation. Measuring the static aerodynamic coefficients normally used to determine component efficiency is discussed. The first topic is testing of two dimensional airfoils at transonic Mach numbers and flight values of Reynolds number. Three dimensional tests of complete configurations and sidewall mounted wings are also described. Since flight Reynolds numbers are of interest, free transition must be allowed. A discussion is given of wind tunnel and model construction effects on transition location. Time dependent phenomena, fluid mechanics, and measurement techniques are examined. The time dependent, or unsteady, aerodynamic test techniques described include testing for flutter, buffet, and oscillating airfoil characteristics. In describing non-intrusive laser techniques, discussions are given regarding optical access, seeding, forward scatter lasers, two-spot lasers, and laser holography. Methods of detecting transition and separation are reported and a new type of skin friction balance is described.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD, Special Course on Advances in Cryogenic Wind Tunnel Technology; 12 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Recent tests at Langley with a University of Tennessee Space Institute (UTSI) skin friction balance (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The experience at LaRC with the University of Tennessee Space Institute skin friction balances is summarized. The Karman-Schoenherr flat plate skin friction formulation is included for comparison. It is concluded that the balance is capable of operation in environments as diverse as cryogenic, transonic, high-shear rate of the 0.3 meter Transonic Cryogenic Tunnel, and high-temperature supersonic environment of the Unitary Plan Wind Tunnel. Proposed new research is outlined.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Research in Natural Laminar Flow and Laminar-Flow Control, Part 2; p 407-411
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Transonic unsteady pressure measurements on a supercritical airfoil at high Reynolds numbers (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 605-614
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Magnets promise productivity (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The use of advanced magnetic suspension and balance systems (MSBS) in wind tunnels is examined. The advantages of MSBS are discussed, including accurate dynamic stability and free manipulation of the model aircraft allowing the free-flying model to respond dynamically to aerodynamic forces. Examples of wind tunnel tests employing MSBS are presented, including tests of a hypersonics parasol wing configuration and the simulation of the ejection of the crew-escape module from an aircraft.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Aerospace America (ISSN 0740-722X); 27; 34-36
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Evaluation of a three-dimensional Navier-Stokes solver for transonic flow over a low-aspect-ratio wing mounted in a wind tunnel (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A three dimensional Navier-Stokes solver is evaluated for transonic flow over a thin, swept, low-aspect ratio wing. The computational study was undertaken in support of a wind tunnel experimental program. The computational results are compared to experimental surface pressure data obtained in a cryogenic wind tunnel with an adaptive wall test section. The results show favorable agreement over a wide range of conditions, further the numerical results provide additional data of the complex three-dimensional flow field. Differences in the predictions and experiment suggest a need to conduct further experiments to evaluate the adaptive wall testing technique, and to model the tunnel sidewall boundary layer in the computations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1725
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Comparison of cryogenic wind tunnel, flight, and computational results for a thin, low-aspect-ratio wing (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A research program was conducted at NASA Langley Research Center to build and test a thin, pressure instrumented wing. The wing chosen was the canard of the X-29, which has a maximum thickness of 5 percent of chord. The wing has 90 pressure taps and was built utilizing an advanced laminated metal technique. It was tested in the 0.3-Meter Transonic Cryogenic Tunnel at transonic Mach numbers and over a wide range of Reynolds number. The data are compared with flight data and Navier-Stokes computational results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1626
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Propulsion simulator for magnetically-suspended wind tunnel models (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of phase two of a current investigation sponsored by NASA Langley Research Center is to demonstrate the measurement of aerodynamic forces/moments, including the effects of exhaust gases, in magnetic suspension and balance system (MSBS) wind tunnels. Two propulsion simulator models are being developed: a small-scale and a large-scale unit, both employing compressed, liquified carbon dioxide as propellant. The small-scale unit was designed, fabricated, and statically-tested at Physical Sciences Inc. (PSI). The large-scale simulator is currently in the preliminary design stage. The small-scale simulator design/development is presented, and the data from its static firing on a thrust stand are discussed. The analysis of this data provides important information for the design of the large-scale unit. A description of the preliminary design of the device is also presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace Applications of Magnetic Suspension Technology, Part 1; p 249-280
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    High Reynolds Number tests of the NASA SC(2)-0012 airfoil in the Langley 0.3-meter transonic cryogenic tunnel (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind-tunnel investigation of the NASA SC(2)-0012 airfoil has been conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel. This investigation supplements the two-dimensional airfoil studies of the Advanced Technology Airfoil Test Program. The Mach number was varied from 0.60 to 0.84. The stagnation temperature and pressure were varied to provide a Reynolds number range from 6 to 40 x 10 to the 6th power based on a 6.0-in. (15.24-cm) airfoil chord. No corrections for wind-tunnel wall interference have been made to the data. The aerodynamic results are presented as integrated force and moment coefficients and pressure distributions without any analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-89102 , L-16259 , NAS 1.15:89102
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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