The effect of transition wires on the pressure distribution over a NACA 63A215 aerofoil section
| dc.contributor.author | Harris, K. D. | |
| dc.date.accessioned | 2017-02-06T15:51:39Z | |
| dc.date.available | 2017-02-06T15:51:39Z | |
| dc.date.issued | 1956-02 | |
| dc.description.abstract | Pressure distributions have been measured over the surface of a N.A.C.A. 63A215 aerofoil section to determine the effect of transition wires on the lift and pitching moment characteristics. These tests, which were made at Reynolds numbers of 3 x 10-) and 8 x 10J, showed that with transition left free laminar separation, followed by turbulent re-attachment, occurred at about 604 chord at low incidences. At medium incidence the position of laminar separation and turbulent re-attachment moved rapidly forward giving rise to kinks or non-linearities in the lift curve. The addition of transition wires at 271% chord eliminated the laminar separation at low incidences and thereby caused the lift curve to become more nearly linear. However, the wires resulted in a reduction in the lift-curve slope at the design CL, and a reduction in Climax. Transition wires at 8%, /a or 1% chord were found to have very adverse effects on the aerofoil characteristics. In particular the lift curves were made very non-linear, and CL max was reduced. The non-linearity was caused by sudden changes in the boundary layer with change of incidence. | en_UK |
| dc.identifier.uri | http://dspace.lib.cranfield.ac.uk/handle/1826/11388 | |
| dc.language.iso | en | en_UK |
| dc.publisher | College of Aeronautics | en_UK |
| dc.relation.ispartofseries | CoA/N-41 | en_UK |
| dc.relation.ispartofseries | 41 | en_UK |
| dc.title | The effect of transition wires on the pressure distribution over a NACA 63A215 aerofoil section | en_UK |
| dc.type | Report | en_UK |