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Effects of aspect ratio on air flow at high subsonic mach numbers (Document No: 19930083187)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1952 |
| Description | Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to 2 on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation. |
| File Size | 4791792 |
| Page Count | 11 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930083187 |
| Archival Resource Key | ark:/13960/t82k0s77h |
| Language | English |
| Publisher Date | 1952-07-01 |
| Access Restriction | Open |
| Subject Keyword | Flow, Mixed Wings, Complete - Aspect Ratio Mach Number Effects - Wing Sections Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |