Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body Metadata
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- Main Title Investigation at supersonic speeds of an inlet employing conical flow separation from a probe ahead of a blunt body
- Series Title NACA Research Memorandums
Author: Hearth, Donald P.Creator Type: Personal
Author: Gorton, Gerald C.Creator Type: Personal
Originator: Lewis Flight Propulsion LaboratoryContributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab
- Creation: 1953-01-19
- Content Description: Report presenting an investigation in the supersonic wind tunnel on an inlet employing conical flow separation from a probe extending upstream from a hemispherical-nosed centerbody. Pressure-recovery and drag characteristics for the inlet were very nearly comparable with a conical-spike inlet, but compared less favorably at Mach numbers below 2.0. A large reduction in pressure recovery and mass flow was obtained at angle of attack.
- Physical Description: 32 p. : ill.
- Keyword: aircraft inlets
- Keyword: flow separation
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: 93R16758
- URL: http://hdl.handle.net/2060/19930087468
- Report No.: NACA-RM-E52K18
- Center for AeroSpace Information Number: 19930087468
- Archival Resource Key: ark:/67531/metadc59520