Bifurcations in the transonic flow past a symmetric airfoil
- 39 Downloads
Transonic flow past an airfoil with a small curvature in its midchord region is numerically investigated. The branching of the stationary solutions of the Euler equations is established and attributed to flow instability at certain angles of attack and freestream Mach numbers. The dependence of the lift coefficient on these parameters is studied.
Keywordsairfoil local supersonic zones instability bifurcations
Unable to display preview. Download preview PDF.
- 1.A. G. Kuz’min, “Interaction of a shock wave with the sonic line,” in: IUTAM Symp. Transsonicum IV, Kluwer, Dordrecht (2003), p. 13.Google Scholar
- 2.A. G. Kuz’min and A. V. Ivanova, “Unstable regimes of inviscid transonic flow in a channel,” Mat. Model., 16, No. 10, 35 (2004).Google Scholar
- 6.A. G. Kuz’min, “Bifurcation of transonic flow over a flattened airfoil,” in: D. A. Caughey and M. M. Hafez (eds.), Frontiers of Fluid Mechanics, World Scient. Publ. Co. Ltd (2005), p. 285.Google Scholar
- 7.A. G. Kuz’min and A. V. Ivanova, “Structural instability of transonic flow past an airfoil,” Inzh.-Fiz. Zh., 77, No. 5, 134 (2004).Google Scholar
- 9.B. Mohammadi, “Fluid dynamics computation with NSC2KE: an user guide, release 1.0”, INRIA Techn. Rep. No. RT-0164 (1994).Google Scholar
- 10.M. Delanyae, Ph. Geuzaine, and J. A. Essers, “Development and application of quadratic reconstruction schemes for compressible flows on unstructured adaptive grids,” AIAA Paper No. 2120 (1997); 13th AIAA Conf. Snowmass (1997), p. 250.Google Scholar