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  • 1
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    Modification to the Langley 8-foot high temperature tunnel for hypersonic propulsion testing (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Described are the modifications currently under way to the Langley 8-Foot High Temperature Tunnel to produce a new, unique national resource for testing hypersonic air-breathing propulsion systems. The current tunnel, which has been used for aerothermal loads and structures research since its inception, is being modified with the addition of a LOX system to bring the oxygen content of the test medium up to that of air, the addition of alternate Mach number capability (4 and 5) to augment the current M=7 capability, improvements to the tunnel hardware to reduce maintenance downtime, the addition of a hydrogen system to allow the testing of hydrogen powered engines, and a new data system to increase both the quantity and quality of the data obtained.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-100486 , NAS 1.15:100486 , AIAA PAPER 87-1887
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    New method for determining heats of combustion of gaseous hydrocarbons (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a spin off of a system developed for monitoring and controlling the oxygen concentration in the Langley 8-foot High Temperature Tunnel, a highly accurate on-line technique was developed for determining heats of combustion of natural gas samples. It is based on measuring the ratio m/n, where m is the (volumetric) flowrate of oxygen required to enrich the carrier air in which the test gas flowing at the rate n is burned, such that the mole fraction of oxygen in the combustion product gases equals that in the carrier air. The m/n ratio is directly related to the heats of combustion of the saturated hydrocarbons present in the natural gas. A measurement of the m/n ratio for the test gas can provide a direct means of determination of its heat of combustion by using the calibration graph relating the m/n values for pure saturated hydrocarbons with their heats of combustion. The accuracy of the technique is determine solely by the accuracy with which the flowrates m and n can be measured and is of the order of 2 percent in the present study. The theoretical principles and experimental results are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TP-2531 , L-16054 , NAS 1.60:2531
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Mass spectrometric gas composition measurements associated with jet interaction tests in a high-enthalpy wind tunnel (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Knowledge of test gas composition is important in wind-tunnel experiments measuring aerothermodynamic interactions. This paper describes measurements made by sampling the top of the test section during runs of the Langley 7-Inch High-Temperature Tunnel. The tests were conducted to determine the mixing of gas injected from a flat-plate model into a combustion-heated hypervelocity test stream and to monitor the CO2 produced in the combustion. The Mass Spectrometric (MS) measurements yield the mole fraction of N2 or He and CO2 reaching the sample inlets. The data obtained for several tunnel run conditions are related to the pressures measured in the tunnel test section and at the MS ionizer inlet. The apparent distributions of injected gas species and tunnel gas (CO2) are discussed relative to the sampling techniques. The measurements provided significant real-time data for the distribution of injected gases in the test section. The jet N2 diffused readily from the test stream, but the jet He was mostly entrained. The amounts of CO2 and Ar diffusing upward in the test section for several run conditions indicated the variability of the combustion-gas test-stream composition.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: NASA-TM-87642 , L-16074 , NAS 1.15:87642
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Tests of a protective shell passive release mechanism for hypersonic wind-tunnel models (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A protective shell mechanism for wind tunnel models was developed and tested. The mechanism is passive in operation, reliable, and imposes no new structural design changes for wind tunnel models. Methods of predicting the release time and the measured loads associated with the release of the shell are given. The mechanism was tested in a series of wind tunnel tests to validate the removal process and measure the pressure loads on the model. The protective shell can be used for wind tunnel models that require a step input of heating and loading such as a thin skin heat transfer model. The mechanism may have other potential applications.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Johnson Space Center The 13th Aerospace Mech. Symp.; p 167-181
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  • 5
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    New technique for calibrating hydrocarbon gas flowmeters (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique for measuring calibration correction factors for hydrocarbon mass flowmeters is described. It is based on the Nernst theorem for matching the partial pressure of oxygen in the combustion products of the test hydrocarbon, burned in oxygen-enriched air, with that in normal air. It is applied to a widely used type of commercial thermal mass flowmeter for a number of hydrocarbons. The calibration correction factors measured using this technique are in good agreement with the values obtained by other independent procedures. The technique is successfully applied to the measurement of differences as low as one percent of the effective hydrocarbon content of the natural gas test samples.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-85792 , L-15788 , NAS 1.15:85792
    Format: application/pdf
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  • 6
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    Proposed fast-response oxygen monitoring and control system for the Langley 8-foot high-temperature tunnel (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A fast-response oxygen monitoring and control system, based on a Y2O3-stabilized ZrO2 sensor, was developed and tested in the laboratory. The system is capable of maintaining oxygen concentration in the CH4-O2-air combustion product gases at 20.9 + or - 1.0 percent. If the oxygen concentration in the exhaust stream differs from that in normal air by 25 percent or more, an alarm signal is provided for automatic tunnel shutdown. The overall prototype system response time was reduced from about 1 sec in the original configuration to about 0.2 sec. The basis of operation and the results of laboratory tests of the system are described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TP-2218 , L-15666 , NAS 1.60:2218
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Fast-Response Oxygen-Monitoring and Control System (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Oxygen sensor is Y2O3-stabilized ZrO2 ceramic disk maintained at 843 degrees C. Overall system response time reduced to about 0.2 second, equal to or less than 1 percent of tunnel run time. When test gas oxygen concentration differs from normal air concentration by 25 percent or more, alarm sounds, and emergency tunnel shutdown signal operates. New ZrO2 sensors intended for hypersonic-vehicle testing.
    Keywords: MATERIALS
    Type: LAR-13257 , NASA Tech Briefs (ISSN 0145-319X); 9; 4; P. 105
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Ceramic and coating applications in the hostile environment of a high temperature hypersonic wind tunnel (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A Mach 7, blowdown wind tunnel was used to investigate aerothermal structural phenomena on large to full scale high speed vehicle components. The high energy test medium, which provided a true temperature simulation of hypersonic flow at 24 to 40 km altitude, was generated by the combustion of methane with air at high pressures. Since the wind tunnel, as well as the models, must be protected from thermally induced damage, ceramics and coatings were used extensively. Coatings were used both to protect various wind tunnel components and to improve the quality of the test stream. Planned modifications for the wind tunnel included more extensive use of ceramics in order to minimize the number of active cooling systems and thus minimize the inherent operational unreliability and cost that accompanies such systems. Use of nonintrusive data acquisition techniques, such as infrared radiometry, allowed more widespread use of ceramics for models to be tested in high energy wind tunnels.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA-TM-81931
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A System for Controlling the Oxygen Content of a Gas Produced by Combustion (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mixture of air, CH4 and OH(2) is burned in a combustion chamber to produce a product gas in the test section. The OH(2) content of the product gas is compared with the OH(2) content of reference air in an OH(2) sensor. If there is a difference an error signal is produced at the output of a control circuit which by the means of a solenoid valve, regulates the flow of OH(2) into the combustion chamber to make the error signal zero. The product gas in the test section has the same oxygen content as air.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: NAS 1.71:LAR-13257-1
    Format: application/pdf
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  • 10
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    Experimental performance of an ablative material as an external insulator for a hypersonic research aircraft (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An ablative material composed of silica-filled elastomeric silicone was tested to evaluate its thermal and structural performance as an external insulator, or heat shield, for a hypersonic research aircraft. The material was also tested to determine whether it would form a durable char layer when initially heated and thereafter function primarily as an insulator with little further pyrolysis or char removal. Aerothermal tests were representative of nominal Mach 6 cruise conditions of the aircraft, and additional tests were representative of Mach 8 cruise and interference heating conditions. Radiant heating tests were used to simulate the complete nominal Mach 6 surface-temperature history. The silica char that formed during aerothermal tests was not durable. The char experienced a general and preferential surface recession, with the primary mechanism for char removal being erosion. Tests revealed that radiant heating is not a valid technique for simulating aerodynamic heating of the material.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TN-D-8490 , L-11148
    Format: application/pdf
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