Item Details

Flight-Test Results From Two Total Temperature Probes for Air-Data Measurements Up to 2014 ̊K (3625 ̊R)

Jack Nugent, Glenn M. Sakamoto, and Lannie D. Webb
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972.
Language
English
Variant Title
NASA TN D-6748
Flight-test results from 2 total temperature probes for air-data measurements up to 2014 ̊K (3625 ̊R)
Series
NASA Technical Note
Summary
An experimental temperature probe package containing a fluidic oscillator temperature probe and a shielded thermocouple temperature probe was tested during several X-15 flights. The X-15 flights provided greatly varying test conditions, including a wide range of rapidly changing total temperatures and Mach numbers which extended from subsonic to hypersonic speeds. Within restricted ranges of free-stream Mach number, free-stream unit weight flow, and local stagnation pressure, both probes yielded ramp outputs of temperature parallel to ramp inputs of free-stream total temperature. Within these ranges both probes were used to determine total temperature in the Mach 6 temperature environment. Because ambient temperature was known, both probes were used to estimate velocity and Mach number.
Description
51 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
Includes bibliographical references (p. 14).
Series Statement
NASA technical note ; D-6748
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Flight-test results from two total temperature probes for air-data measurements up to 2014 ̊K (3625 ̊R) c| Jack Nugent, Glenn M. Sakamoto, and Lannie D. Webb.
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    a| NASA TN D-6748
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    3
      
    a| Flight-test results from 2 total temperature probes for air-data measurements up to 2014 ̊K (3625 ̊R)
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    a| Washington, D.C. : b| National Aeronautics and Space Administration : b| [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], c| 1972.
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    a| 51 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| D-6748
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    a| Includes bibliographical references (p. 14).
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    a| An experimental temperature probe package containing a fluidic oscillator temperature probe and a shielded thermocouple temperature probe was tested during several X-15 flights. The X-15 flights provided greatly varying test conditions, including a wide range of rapidly changing total temperatures and Mach numbers which extended from subsonic to hypersonic speeds. Within restricted ranges of free-stream Mach number, free-stream unit weight flow, and local stagnation pressure, both probes yielded ramp outputs of temperature parallel to ramp inputs of free-stream total temperature. Within these ranges both probes were used to determine total temperature in the Mach 6 temperature environment. Because ambient temperature was known, both probes were used to estimate velocity and Mach number.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Temperature measurements.
    650
      
    0
    a| Thermocouples.
    650
      
    0
    a| Fluidic devices.
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    a| Space vehicles.
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    1
      
    a| Webb, Lannie D.
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    a| Sakamoto, Glenn M.
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    a| Flight Research Center (U.S.)
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    a| United States. b| National Aeronautics and Space Administration.
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