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  • 1
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    Flow fields, pressure distributions, and heat transfer for delta wings at hypersonic speeds (1960)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: GENERAL
    Type: Joint Conf. on Lifting Manned Hypervelocity and Reentry Vehicles, part 1; p 163-185
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Effects of upstream wall temperatures on hypersonic tunnel wall boundary-layer profile measurements. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA Journal; 11; Apr. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Simultaneous Raman and laser velocimeter measurements (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The feasibility of performing Raman and laser velocimeter measurements simultaneously is demonstrated, and it is shown that the background radiation associated with the Mie scattering and large particulate concentrations does not saturate or distort the relatively weak rotational Raman signals. Under stringent conditions of low static gas densities and large particulate concentrations, Raman density and temperature measurements agree to within plus or minus 5% of the calculated values.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal; 12; Oct. 197
    Format: text
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  • 4
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    Comparison of prediction methods and studies of relaxation in hypersonic turbulent nozzle-wall boundary layers (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-5433
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Preliminary surveys of the wall boundary layer in a Mach 6 axisymmetric tunnel (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Temperature and pressure distributions in boundary layer of hypervelocity flow in straight pipe test section
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-5620 , L-6697
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Processing of the laser Doppler velocimeter signals (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The laser Doppler velocimeter (LDV) is a probeless technique that provides a remote measurement of mean and fluctuating velocities. The measurement is actually obtained from small particles embedded in the flow which scatter light from an illuminating laser beam interference pattern. A portion of this scattered light is collected by a photomultiplier which yields an electronic signal whose frequency is directly proportional to the velocity of the small particles. The purpose of this paper is to describe and critically compare three techniques most used to process this electronic signal. These techniques are: (1) spectrum analyzer - a frequency scanning filter (frequency domain instrument), (2) wide-band frequency tracker - a frequency lock loop (frequency domain instrument), and (3) high-speed frequency counter - an interval timer (time domain instrument). The study determines the ability of each technique to process the LDV signal and yield velocity data to be used in determining the flow characteristics.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ICIASF ''73; International Congress on Instrumentation in Aerospace Simulation Facilities; Sep 10, 1973 - Sep 12, 1973; Pasadena, CA
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  • 7
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    Development of a controllable particle generator for LV seeding in hypersonic wind tunnels (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The paper describes the considerations that went into the development of a controllable particle generator for laser velocimeter seeding in a hypersonic wind tunnel operating at 3.45 million N/sq m, 533 K, and stream speed of about 1000 m/sec. Operating conditions determined the choice of a silicone oil as the material, and the requirement that the particle follow the flow within a certain accuracy range put constraints on the allowable particle size range. The principle of the particle generating device chosen was that of the LaMer generator, in which a liquid is first vaporized, mixed with the carrier gas, and then condensed under carefully controlled conditions. Preliminary results of studies on the effect of various apparatus parameters on the particle median diameter are given.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Minnesota Symposium on Laser Anemometry; Oct 22, 1975 - Oct 24, 1975; Bloomington, MN
    Format: text
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  • 8
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    Laser velocimeter measurements in a large transonic wind tunnel (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A two-component fringe type laser velocimeter operated in the backscatter mode was used to measure the free-stream velocity in an undisturbed flow field in a wind-tunnel test section from Mach 0.2 to Mach 1.0 and to measure the velocity along the stagnating streamline of a hemisphere model from Mach 0.2 to Mach 0.8. Burst signals from the laser velocimeter were processed by high-speed burst counters, and histograms of the number of occurrences of a particular counter output were collected by means of a pulse height analyzer. Arithmetic means of the histograms were calculated, and the results were compared with predicted local gas velocities with allowance for the lag of the scattering particles with respect to the gas flow. The free-stream measurements were accurate to within 2% of the calibration measurements. The stagnation streamline measurements show trends similar to theoretical predictions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Minnesota Symposium on Laser Anemometry; Oct 22, 1975 - Oct 24, 1975; Bloomington, MN
    Format: text
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  • 9
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    Direct measurements at Mach 6 of turbulent skin-friction reduction by injection from single and multiple flush slots (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The surface skin-friction reduction downstream of one to four successive flush slots injecting at an angle of 10 deg into a turbulent Mach 6 boundary layer has been determined from direct measurements of surface shear. Increasing the number of succeeding slots increases the skin-friction reduction, but this trend reverses at high injection rates. The incremental improvement in skin-friction reduction decreases with increasing number of slots. Comparison with previously reported step slot data indicates that step slots with tangential injection are more effective in reducing skin friction than the present flush slot configuration. Finite-difference predictions are in reasonable agreement with skin-friction and boundary-layer profile data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-178 , Aerospace Sciences Meeting; Jan 26, 1976 - Jan 28, 1976; Washington, DC
    Format: text
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  • 10
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    A feasibility test of the laser velocimeter in the Mach 5 nozzle test chamber (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A one-component, fringe type laser velocimeter in the backscatter mode was used to measure flow velocities from 732 to 792 m/sec about a shock from an inclined flat plate in a Mach 5 tunnel. This test was chosen to determine system characteristics in applying the laser velocimeter to measure velocities in hypersonic flow fields. The seeding particles, less than 20 microns in diameter, were injected into the tunnel supply pipe, approximately 1 meter upstream of the nozzle throat, through a rake along the diameter. The LV signals were processed by two methods, a scanning spectrum analyzer and a high-speed counter. The measured velocity distributions obtained were analyzed to determine the errors due to particle lag, transit time broadening and high-speed counter quantizing error.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: International Workshop on Laser Velocimetry; Mar 27, 1974 - Mar 29, 1974; West Lafayette, IN
    Format: text
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