Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets Metadata
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- Main Title Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets
- Series Title NACA Research Memorandums
Author: Valerino, Alfred S.Creator Type: Personal
Originator: Lewis Flight Propulsion LaboratoryContributor Type: OrganizationContributor Info: National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab
- Creation: 1952-12-08
- Content Description: Report presenting an investigation in the 8- by 6-foot supersonic tunnel at a range of free-stream Mach numbers at zero angle of attack to determine the effects of internal corner fillets on the pressure recovery characteristics of twin-scoop conical-type inlets utilizing boundary layer removal and mounted on the RM-10 body. Without boundary layer removal, the use of fillets resulted in substantial improvements in pressure recoveries and near critical mass flows up to a certain Mach number.
- Physical Description: 14 p. : ill.
- Keyword: corner fillets
- Keyword: aircraft inlets
- Keyword: aerodynamics
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: 93R19627
- URL: http://hdl.handle.net/2060/19930090337
- Report No.: NACA-RM-E52J10
- Center for AeroSpace Information Number: 19930090337
- Archival Resource Key: ark:/67531/metadc64540