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Reynolds number and leading-edge bluntness effects on a 65 deg delta wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Luckring, J. M. |
| Copyright Year | 2002 |
| Description | A 65 degree delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic chord Reynolds numbers from 6 million to 120 million at subsonic and transonic speeds. The configuration incorporated systematic variation of the leading edge bluntness. The analysis for this paper is focused on the Reynolds number and bluntness effects at subsonic speeds (M = 0.4) from this data set. The results show significant effects of both these parameters on the onset and progression of leading-edge vortex separation. |
| File Size | 579115 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20040139871 |
| Archival Resource Key | ark:/13960/t75t8kr4d |
| Language | English |
| Publisher Date | 2002-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Vortices Reynolds Number Delta Wings Transonic Wind Tunnels Pressure Distribution Airfoils Aircraft Design Wind Tunnel Models Angle of Attack Spanwise Blowing Blunt Leading Edges Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
