Computational investigation of incompressible airfoil flows at high angles of attack
| dc.contributor.advisor | Platzer, Max F. | |
| dc.contributor.author | Mathre, John Mark | |
| dc.date | December 1988 | |
| dc.date.accessioned | 2012-11-27T18:06:23Z | |
| dc.date.available | 2012-11-27T18:06:23Z | |
| dc.date.issued | 1988-12 | |
| dc.identifier.uri | http://hdl.handle.net/10945/22965 | |
| dc.description.abstract | Cebeci's viscous/inviscid interaction program was applied to the analysis of steady, two dimensional, incompressible flow past four airfoils, the NACA 66₃-018, 0010 (Modified), 4412 and the Wortmann FX 63-137. Detailed comparisons with the available experimental results show that the essential features are correctly modelled, but that significant discrepancies are found in regions of flow separations. | |
| dc.description.uri | http://archive.org/details/computationalinv1094522965 | |
| dc.format.extent | 143 p. | en_US |
| dc.language.iso | en_US | |
| dc.publisher | Monterey, California. Naval Postgraduate School | en_US |
| dc.rights | This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States. | |
| dc.title | Computational investigation of incompressible airfoil flows at high angles of attack | en_US |
| dc.type | Thesis | en_US |
| dc.contributor.secondreader | Howard, R.M. | |
| dc.contributor.corporate | Naval Postgraduate School (U.S.) | |
| dc.contributor.department | Aeronautics and Astronautics | |
| dc.subject.author | computational analysis of inviscid | |
| dc.subject.author | viscous and interaction schemes | |
| dc.description.service | Lieutenant, United States Navy | |
| etd.thesisdegree.name | M.S. in Aeronautical Engineering | en_US |
| etd.thesisdegree.level | Masters | en_US |
| etd.thesisdegree.discipline | Aeronautical Engineering | en_US |
| etd.thesisdegree.grantor | Naval Postgraduate School | en_US |
| dc.description.distributionstatement | Approved for public release; distribution is unlimited. |
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