Comparison of the minimum drag of two versions of a modified delta-wing fighter as obtained from flight tests of rocket-boosted models and equivalent bodies between Mach numbers of 0.80 and 1.64 Metadata
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- Main Title Comparison of the minimum drag of two versions of a modified delta-wing fighter as obtained from flight tests of rocket-boosted models and equivalent bodies between Mach numbers of 0.80 and 1.64
- Series Title NACA Research Memorandums
Author: Hasting, Earl C., Jr.Creator Type: Personal
Author: Mitcham, Grady L.Creator Type: Personal
Originator: Langley Aeronautical LaboratoryContributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Langley Aeronautical Lab
- Creation: 1956-09-24
- Content Description: Report presenting an investigation to determine the reduction in minimum drag that could be obtained at supersonic speeds by redesigning the fuselage and reducing the wing and tail thickness of a modified delta-wing fighter-type airplane. Results regarding the mass-flow ratio, total-pressure recovery, and drag are provided.
- Physical Description: 24 p. : ill.
- Keyword: drag reduction
- Keyword: aircraft design
Name: National Advisory Committee for Aeronautics CollectionCode: NACA
Name: Technical Report Archive and Image LibraryCode: TRAIL
Name: UNT Libraries Government Documents DepartmentCode: UNTGD
- Rights Access: public
- Rights License: pd
- Rights Statement: No Copyright, Unclassified, Unlimited, Publicly available
- Accession or Local Control No: 93R18706
- URL: http://hdl.handle.net/2060/19930089416
- Report No.: NACA-RM-L56E04
- Center for AeroSpace Information Number: 19930089416
- Archival Resource Key: ark:/67531/metadc62790