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  • 1995-1999  (2)
  • 1
    facet.materialart.
    Unknown
    Experimental Demonstration of the Use of a N2O/N2 Mixture in the Driven Tube of a Reflected Shock Tunnel in Order to Increase Test Time (1996)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: An experimental investigation was carried out into the replacement of air in the driven tube of a reflected shock tunnel by an N2O/N2 mixture in order to increase the test time. The incident shock velocities were between 2 and 3 km/sec. Test times were estimated from light emission histories in the driven tube (at distance of L/D = 46.5 from the main diaphragm) and in the nozzle at an area ratio of 27.9 and from pressure histories just upstream of the nozzle entrance (at L/D = 54). The test times estimated from the light emission histories in the driven tube showed that consistent increases of 60-100% were obtained upon substituting N2O/N2 for air in the driven tube. These increases were in very good agreement with theoretical estimates. The test times estimated from the light emission histories in the nozzle or pressure histories at the nozzle inlet showed significant improvements with N2O/N2 only for cases where the facility was operated at substantially overtailored conditions. It is believed that this is due to the greater stability of the driver-driven interface at overtailored operating conditions. At overtailored operating conditions, test times increases of 60-100% with N2O/N2 were observed with all three diagnostic techniques. These increases were in reasonable agreement with theoretical estimates.
    Keywords: Fluid Mechanics and Thermodynamics
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Review Of Existing Facilities: Shock Tunnels, Part of AIAA Short Course On Aerothermodynamic Facilities and Applications (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: This review is divided into two main sections. The first section described the various types of shock tunnel facilities - reflected shock tunnels, non-reflected shock tunnels and expansion tubes/tunnels. Driver technology is then described, followed by a discussion of the performance obtainable from various driver-driven combinations. A survey of a number of facilities is then presented. The second part of the review deals with details of the operation of the facilities. Operation of combustion drivers, electrically heated drivers and piston compression drivers is discussed in some detail. Main diaphragm break techniques are discussed, with particular attention being paid to maintaining the integrity of the diaphragm petals. Secondary diaphragm techniques are discussed. Phenomena which limit test time are discussed and a number of techniques to increase test time are presented. Contamination of the flow with material ablated from the wall is discussed along with the relative suitability of various materials for lining the tubes and nozzle. Finally, boundary layer effects in shock tunnels and expansion tubes are discussed.
    Keywords: Research and Support Facilities (Air)
    Type: Aerothermodynamic Facilities and Applications; Jun 23, 1995 - Jun 24, 1995; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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