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Experimental pressure distributions over wing tips at mach number 1.9 i : wing tip with subsonic leading edge
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1949 |
| Description | An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attack up to 8 degrees. Pressures on the top surface nearest the subsonic edge indicated local expansions beyond values predicted by linearized theory. |
| File Size | 14616581 |
| Page Count | 30 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930085537 |
| Archival Resource Key | ark:/13960/t4wh6x06g |
| Language | English |
| Publisher Date | 1949-01-27 |
| Access Restriction | Open |
| Subject Keyword | Flow, Supersonic Mach Number Effects - Wing Section Loads, Steady Aerodynamic - Wings Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
