Item Details

Atomization, Drop Size, and Penetration for Cross-Stream Water Injection at High-Altitude Reentry Conditions With Application to the RAM C-I and C-III Flights

by Paul B. Gooderum and Dennis M. Bushnell
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration ; [Springfield, Va. : For sale by the National Technical Information Service], 1972.
Language
English
Series
NASA Technical Note
Summary
Atomization, drop size, and penetration data are presented for cross stream water injection at conditions simulating high altitude reentry (low Weber number, high static temperature, high Knudsen number, and low static pressure). These results are applied to the RAM C-1 and C-3 flights. Two primary breakup modes are considered, vapor pressure or flashing and aerodynamic atomization. Results are given for breakup boundaries and mean drop size for each of these atomization mechanisms. Both standard and flight orifice geometries are investigated. The data were obtained in both a static environment and in conventional aerodynamic facilities at Mach numbers of 4.5 and 8. The high temperature aspects of reentry were simulated in a Mach 5.5 cyanogen-oxygen tunnel with total temperature of 4500 K.
Description
53 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
  • Prepared at Langley Research Center.
  • Cover title.
  • Bibliography: p. 53.
Series Statement
NASA technical note ; NASA TN D-6747
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

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    a| Atomization, drop size, and penetration for cross-stream water injection at high-altitude reentry conditions with application to the RAM C-I and C-III flights c| by Paul B. Gooderum and Dennis M. Bushnell.
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    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [Springfield, Va. : b| For sale by the National Technical Information Service], c| 1972.
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    a| 53 p. : b| ill. ; c| 27 cm.
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    a| NASA technical note ; v| NASA TN D-6747
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    a| Prepared at Langley Research Center.
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    a| Bibliography: p. 53.
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    a| Atomization, drop size, and penetration data are presented for cross stream water injection at conditions simulating high altitude reentry (low Weber number, high static temperature, high Knudsen number, and low static pressure). These results are applied to the RAM C-1 and C-3 flights. Two primary breakup modes are considered, vapor pressure or flashing and aerodynamic atomization. Results are given for breakup boundaries and mean drop size for each of these atomization mechanisms. Both standard and flight orifice geometries are investigated. The data were obtained in both a static environment and in conventional aerodynamic facilities at Mach numbers of 4.5 and 8. The high temperature aspects of reentry were simulated in a Mach 5.5 cyanogen-oxygen tunnel with total temperature of 4500 K.
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    a| Mode of access: Internet.
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    a| Atomization.
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    a| Space vehicles x| Aerodynamics.
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    a| Space vehicles x| Atmospheric entry.
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    a| Aerodynamics.
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    a| Bushnell, Dennis M.
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    a| United States. b| National Aeronautics and Space Administration.
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    a| Langley Research Center.
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