Abstract
The paper presents a comparison between the numerical results of three different flow solvers, each of them implementing a different modelling strategy, on the same Fenestron® geometry of the EC 135 Helicopter. A comparison in terms of power versus thrust between all predictions results and the test bench measurements available at Eurocopter [2] is shown. A deeper analysis of the local aerodynamic inside the EC 135 Fenestron®, as computed by the most complex methodology, is also shown. The paper concludes by listing advantages and limitations of each computational strategy and suggesting a strategy for each possible industrial application.
| Original language | English |
|---|---|
| Pages (from-to) | 20-28 |
| Number of pages | 9 |
| Journal | Annual Forum Proceedings - AHS International |
| Volume | 1 |
| State | Published - 2008 |
| Event | 64th Annual Forum - AHS International - Montreal, Canada Duration: 29 Apr 2008 → 1 May 2008 |