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  • 1
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    Refinement of an 'alternate' method for measuring heating rates in hypersonic wind tunnels (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Recently obtained hypersonic wind tunnel results are presented which resolve the principal uncertainty associated with the use of thin film gages on substrates of the glass ceramic substance designated MACOR.THe uncertainty is with respect to both MACOR's thermal properties and the variation of these properties with temperature. The relatively large influence of shock strength on stagnation point heating at low Reynolds numbers is illustrated.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA Journal (ISSN 0001-1452); 23; 810-812
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flow-establishment times for blunt bodies in an expansion tube (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Flow establishment results are presented as obtained from shock standoff distance, pressure, and heat transfer measurements in the Langley expansion tube. The models tested were flat-faced cylinders with varying radius and a sphere with a constant radius, and they were positioned at the acceleration section exit and tested in the open jet at zero angle of attack. The experimental results were obtained as spinoff from various studies using helium, air, and CO2 test gases at freestream velocities in the range 5-7 km/sec. Time histories of shock detachment distance illustrate that the shock formation about the smaller-radii flat-faced cylinders and the sphere is symmetrical, whereas a complex, asymmetric formation is observed for the larger-radii cylinders. Flow is shown to establish more readily about the sphere than a flat-faced cylinder of the same diameter. A quasi-steady flow exists about relatively large blunt models during two-thirds of the approximate 250-microsec expansion tube test period.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA Journal; 13; Dec. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Expansion tunnel performance with and without an electromagnetically opened tertiary diaphragm (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A study was conducted to examine the effect of synchronization of an electromagnetically opened tertiary diaphragm with flow arrival at the diaphragm on the pitot pressure measured at the test section of an expansion tunnel. The effect of tertiary diaphragm pressure ratio (ratio of initial nozzle pressure to quiescent acceleration section pressure) on the pitot pressure time history is also determined. The inadequacy of a pressure transducer protection arrangement used in previous expansion tube and expansion tunnel tests was revealed.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA Journal; 15; July 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Hypersonic aerodynamic/aerothermodynamic testing capabilities at Langley Research Center (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Capabilities of the Langley Hypersonic Facilities Complex that consists of nine blowdown-to-vacuum wind tunnels are reviewed. These tunnels complement one another to provide ranges of Mach number from 6 to 20, unit Reynolds number from 0.03 to 40 million per ft, and normal shock density ratio from 2 to 12. Topics under consideration include the basic components of each facility, status, and upgrades recently performed; instrumentation and testing techniques routinely used to measure forces and moments, surface pressures, surface temperature-time histories, flow properties within the shock layer about the model via survey probes, and flow visualization; and data acquisition systems and upgrades performed via a NASA revitalization program.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 92-3937
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Langley hypersonic facilities complex - Description and application (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Langley Hypersonic Facilities Complex (HFC) consists of hypersonic, blowdown wind tunnels developed and put into operation between the late 1950's and early 1970's. These facilities complement one another to presently provide ranges of Mach number from 6 to 22, unit Reynolds number from 0.1 to 15 million per foot, and normal shock density ratio from 4 to 12. Descriptions of these facilities are presented along with the testing techniques routinely used. Examples of the application of the HFC to generate data bases for proposed entry vehicles and for the verification of computer codes are given. Plans to upgrade the facilities to improve flow quality, productivity, capability and reliability are discussed.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 86-0741
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Langley hypersonic aerodynamic/aerothermodynamic testing capabilities - Present and future (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Langley Hypersonic Facilities Complex consists of nine hypersonic, blowdown-to-vacuum wind tunnels that complement one another to provide a range of Mach number from 6 to 22, with Reynolds number from 0.03 to 40 million per foot and, most importantly for blunt configurations, a normal shock density ratio from 4 to 12. Presently, most of these facilities are receiving modifications and upgrades to hardware components and instrumentation to increase their capability, reliability, and productivity. Descriptions and capabilities of these facilities are presented along with measurement techniques routinely used. Future facility plans are discussed, with the focus on an Advanced Hypervelocity Aerophysics Facility being proposed for construction in the mid-1990s.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 90-1376
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Operational experience in the Langley expansion tube with various test gases (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Langley Expansion Tube is an operational facility capable of producing good quality, highly repeatable, quasi-steady flow for test times sufficient to establish flow about blunt axisymmetric and two-dimensional models. Due to the capability of testing with arbitrary test gases, a wide range of real-gas, hypersonic-hypervelocity flow conditions may be generated. However, for a given test gas, the range of operating conditions producing useful flow is shown to be rather limited; hence, the facility yields a given flow condition for a given test gas, and variation in flow conditions comes about by using different test gases. Data are presented for operations using air and carbon dioxide as test gases. The driver gas was unheated helium at a nominal pressure of 5000 psi (34.5 MN sq m).
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-78637
    Format: application/pdf
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  • 8
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    Dosimetry of low energy proton beams for use in spacecraft parts testing (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Thermoluminescent Dosimeters tes (TLD) were used to measure proton fluences consisting of 5MeV or lower energies. The results were at variance with the corresponding gamma measurements. The results of experiments on low energy proton dosimetry using LiF-in-teflon microrods (TLD-700 or LiF-7), are presented.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: PAPER-11 , NASA. Goddard Space Flight Center 8th Conf. on Space Simulation; p 153-154
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Description and preliminary calibration results for the Langley hypersonic CF4 tunnel (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed description of the hypersonic CF4 tunnel is presented along with discussion of the basic components, instrumentation, and operating procedure. Operational experience with the CF4 reclaimer and lead-bath heater is discussed. Comparison of measured and predicted shock detachment distance on a sphere and pressure distributions measured on a sharp leading-edge flat plate revealed the absence of significant flow nonuniformity and lent creditability to predicted free stream flow conditions. The economic operation of this facility centers about the CF4 reclaimer, which was designed to operate at an efficiency of 90 to 95 percent. A number of modifications were made to the reclaimer system to improve its performance, and presently, the system reclaims approximately 75 percent of the test gas. Even with current budgetary constraints, this efficiency permits the CF4 tunnel to be operated as a viable research wind tunnel.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-78800
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    A critical examination of expansion tunnel performance (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental study of the performance of the expansion tunnel for various test gases and range of quiescent acceleration section and nozzle pressure, nozzle geometric area ratio, and nozzle axial station has been performed. Flow diagnostics used to examine expansion tunnel flow characteristics were time histories and profiles of pitot pressure and axial component of flow velocity. The purpose of this study was to determine experimentally what limitations might restrict predicted operational flexibility and the advantages and disadvantages of this mode of operation as compared to the expansion tube. Results are presented which demonstrate the expansion tunnel offers several advantages over the expansion tube, but the severity of the disadvantages of the tunnel makes the expansion tube mode of operation the more desirable for performing hypersonic-hypervelocity aerothermodynamic studies of proposed entry configurations.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 78-768 , Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
    Format: text
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