A Preliminary Study of Ram-Actuated Cooling Systems for Supersonic Aircraft

One of 5,164 reports in the series: NACA Research Memorandums available on this site.

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Description

An analysis has been made of the characteristics of several cooling cycles suitable for cockpit cooling of supersonic aircraft. All the cycles considered utilize the difference between dynamic and ambient static pressure to actuate the cooling system and require no additional power source. The results of the study indicate that as flight speeds become greater, increasingly complex systems are required to reduce the altitudes above approximately 35,000 feet, a system composed of an externally loaded expansion turbine in conjunction with a supersonic diffuser would maintain tolerable ventilating air temperature, at least up to a flight Mach number of 2. The ... continued below

Physical Description

[38] p. : ill.

Creation Information

Stalder, Jackson R. & Wadleigh, Kenneth R. April 29, 1947.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 37 times . More information about this report can be viewed below.

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  • Main Title: A Preliminary Study of Ram-Actuated Cooling Systems for Supersonic Aircraft
  • Series Title: NACA Research Memorandums

Description

An analysis has been made of the characteristics of several cooling cycles suitable for cockpit cooling of supersonic aircraft. All the cycles considered utilize the difference between dynamic and ambient static pressure to actuate the cooling system and require no additional power source. The results of the study indicate that as flight speeds become greater, increasingly complex systems are required to reduce the altitudes above approximately 35,000 feet, a system composed of an externally loaded expansion turbine in conjunction with a supersonic diffuser would maintain tolerable ventilating air temperature, at least up to a flight Mach number of 2. The most complex system considered,composed of compressor, intercooler, and expansion turbine with the intercooler cooling air decreased in temperature by expansion through an auxiliary turbine is capable of maintaining a ventilation air temperature less than ambient temperature up to a flight Mach number of 3.7.

Physical Description

[38] p. : ill.

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  • URL: http://hdl.handle.net/2060/20030063161 External Link
  • Report No.: NACA-RM-A7C04
  • Center for AeroSpace Information Number: 20030063161
  • Archival Resource Key: ark:/67531/metadc63770

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

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Creation Date

  • April 29, 1947

Added to The UNT Digital Library

  • Nov. 17, 2011, 5:13 p.m.

Description Last Updated

  • Feb. 1, 2018, 10:03 a.m.

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Stalder, Jackson R. & Wadleigh, Kenneth R. A Preliminary Study of Ram-Actuated Cooling Systems for Supersonic Aircraft, report, April 29, 1947; (digital.library.unt.edu/ark:/67531/metadc63770/: accessed September 22, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.