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Effect of compressibility on the flow past a two-dimensional bump
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1952 |
| Description | An investigation has been conducted to determine experimentally the effects of compressibility on the flow past a bump and to compare the experimentally determined results with theory. Pressure measurements and Schlieren photographs were made of the flow past two bumps having thickness-chord ratios of 0.10 and 0.30 at Mach numbers between 0.20 and 0.84 |
| File Size | 17179467 |
| Page Count | 36 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930083054 |
| Archival Resource Key | ark:/13960/t3wt3189f |
| Language | English |
| Publisher Date | 1952-04-01 |
| Access Restriction | Open |
| Subject Keyword | Flow, Subsonic Mach Number Effects - Wing Sections Wing Sections - Thickness Flow, Mixed 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 |