Please use this identifier to cite or link to this item:
|Title:||Time-domain aeroelastic simulation by a coupled euler and integral boundary-layer method|
|Source:||Yang, S.,Zhang, Z.,Liu, F.,Luo, S.,Tsai, H.-M.,Schuster, D.M. (2004). Time-domain aeroelastic simulation by a coupled euler and integral boundary-layer method. Collection of Technical Papers - AIAA Applied Aerodynamics Conference 2 : 1146-1157. ScholarBank@NUS Repository.|
|Abstract:||An interactive boundary-layer method that solves the unsteady Euler equations coupled with Green's lag entrainment integral boundary-layer equations is presented for time domain aeroelastic computation. The three-dimensional unsteady Euler equations are solved on stationary body-fitted curvilinear grids. Unsteady boundary conditions on moving surfaces in an aeroelastic problem are accounted for by using approximate small-perturbation method without moving the computational grid. A semi-inverse method is used to couple the Euler and the boundary-layer solutions in order to compute flows with strong inviscid and viscous interactions. The method is tested on standard steady transonic flow computations for the NACA0012 and RAE2822 airfoils and computations of three-dimensional steady and unsteady flows of the LANN Wing. Comparisons with Navier-Stokes results and available experimental data show that the interactive-boundary-layer method provides significant improvement over inviscid calculations by the Euler equations alone. The proposed method is used to predict the flutter boundary for the Isogai wing test case through time domain simulations. The interactive boundary-layer result agrees with that by a Navier-Stokes solver and indicates fundamental differences between the viscous and inviscid solutions in the transonic range.|
|Source Title:||Collection of Technical Papers - AIAA Applied Aerodynamics Conference|
|Appears in Collections:||Staff Publications|
Show full item record
Files in This Item:
There are no files associated with this item.
checked on Mar 10, 2018
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.