Item Details

Investigation of Net-Thrust and Base-Pressure Characteristics of Cylindrical Afterbodies With Clustered Supersonic Nozzles at Transonic Mach Numbers

by Earl H. Andrews, Jr.
Format
Book; Government Document; Online; EBook
Published
Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
Language
English
Series
NASA Technical Note
Summary
A wind tunnel investigation has been conducted at Mach numbers from 0.9 to 1.4 to determine the net-thrust and base-pressure characteristics of cylindrical afterbodies having clustered supersonic nozzles. The design Mach numbers of the nozzles were 2.0 and 2.5 and the number of clustered bodies ranged from two to six. The nozzles had throat-to-base diameter ratios of 0.155, 0.225, 0.278, and 0.320. Some models were tested with various configurations of extended, shrouded, flush, and canted nozzles. The nozzles discharged unheated air from the base at ratios of jet total pressure to free-stream static pressure ranging from 1 to approximately 20. The results of this investigation showed that both the ratio of total exit area to base area and the number of jets affect the net-thrust factor to a significant degree for the extended-nozzle configurations. Good net-thrust factors were obtained with all the model configurations near the design jet total-pressure-ratio range. Canting the twin nozzles outward resulted in a favorable thrust factor over a limited jet total-pressure-ratio range, and surrounding the nozzles with a single shroud reduced thrust factors for the range of jet total-pressure ratio of this investigation.
Description
46 p. : ill. ; 26 cm.
Mode of access: Internet.
Notes
  • Document ID: 20040006325.
  • "NASA TN D-978."
  • "Langley Research Center, Langley Air Force Base, Va."
  • "November 1961."
  • Cover title.
  • Includes bibliographical references (p. 13).
Series Statement
NASA technical note ; D-978
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

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    a| Investigation of net-thrust and base-pressure characteristics of cylindrical afterbodies with clustered supersonic nozzles at transonic Mach numbers / c| by Earl H. Andrews, Jr.
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    a| Washington, [D.C.] : b| National Aeronautics and Space Administration, c| 1961.
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    a| 46 p. : b| ill. ; c| 26 cm.
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    a| NASA technical note ; v| D-978
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    a| Document ID: 20040006325.
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    a| "NASA TN D-978."
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    a| "Langley Research Center, Langley Air Force Base, Va."
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    a| "November 1961."
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    a| Cover title.
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    a| Includes bibliographical references (p. 13).
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    a| A wind tunnel investigation has been conducted at Mach numbers from 0.9 to 1.4 to determine the net-thrust and base-pressure characteristics of cylindrical afterbodies having clustered supersonic nozzles. The design Mach numbers of the nozzles were 2.0 and 2.5 and the number of clustered bodies ranged from two to six. The nozzles had throat-to-base diameter ratios of 0.155, 0.225, 0.278, and 0.320. Some models were tested with various configurations of extended, shrouded, flush, and canted nozzles. The nozzles discharged unheated air from the base at ratios of jet total pressure to free-stream static pressure ranging from 1 to approximately 20. The results of this investigation showed that both the ratio of total exit area to base area and the number of jets affect the net-thrust factor to a significant degree for the extended-nozzle configurations. Good net-thrust factors were obtained with all the model configurations near the design jet total-pressure-ratio range. Canting the twin nozzles outward resulted in a favorable thrust factor over a limited jet total-pressure-ratio range, and surrounding the nozzles with a single shroud reduced thrust factors for the range of jet total-pressure ratio of this investigation.
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    a| Mode of access: Internet.
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    a| Aerodynamics, Supersonic.
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    a| Supersonic nozzles.
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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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