Afterbody/nozzle pressure distributions of a twin-tail twin-enginer fighter with axisymmetric nozzles at Mach numbers from 0.6 to 1.2
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Author
Contributions
- Langley Research Center. - Contributor
Publication
1995 - National Aeronautics and Space Administration, Langley Research Center, Hampton, Va, Virginia
Language
English
Word Count
52,250 words, Guess
Page Count
209 pages
Identifiers
- OCLC Control Number32881803
- Open LibraryOL17113314M
Alternate Titles
- Afterbody nozzle pressure distributions of a twin-tail twin-enginer fighter with axisymmetric nozzles at Mach numbers from 0.6 to 1.2.
Subjects
Topics
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