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|Title:||Supercritical flow over unstalled plunging airfoil computed by euler method||Authors:||Yang, S.
|Issue Date:||2006||Citation:||Yang, S.,Luo, S.,Liu, F.,Tsai, H.-M. (2006). Supercritical flow over unstalled plunging airfoil computed by euler method. Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting 5 : 3486-3497. ScholarBank@NUS Repository.||Abstract:||The air flow around a flapping airfoil can reach supercritical even when the freestream Mach number is as low as 0.2. The supercritical flow about a sinusoidally plunging airfoil NACA 0012 in a uniform stream parallel to the airfoil chord is studied by the inviscid version of a three-dimensional unsteady compressible Euler/Navier-Stokes flow solver. Fully attached flow is assumed. The Euler solver is validated by a Navier-Stokes solutions at freestream Mach number of 0.3 in the literature, and a dynamic-stall boundary is identified as the minimum pressure coefficient over the airfoil equal to a constant. The instantaneous load distribution is decomposed into harmonic components and compared with the classical linear oscillating-aifoil theory. The effects of the local supersonic-flow region are investigated.||Source Title:||Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting||URI:||http://scholarbank.nus.edu.sg/handle/10635/116128||ISBN:||1563478072|
|Appears in Collections:||Staff Publications|
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