机体/动力装置一体化分析中的动力影响效应数值模拟
Numerical simulation method for the powered effects in airframe/propulsion integration analysis
-
摘要: 采用合适的进、排气边界条件, 对带动力的单独涡扇发动机模型和带动力的DLR-F6翼身架舱复杂组合体(WBPN)模型的流场进行了数值模拟和分析.运用Roe三阶迎风偏置通量差分裂方法和隐式近似因子分解方法求解雷诺平均Navier-Stokes方程, 基于点搭接多块网格技术生成高质量计算网格, 通过多重网格技术来加速收敛.着重对动力发动机进、排气边界条件的给定进行了推导, 以准确地模拟发动机动力效应.计算结果与实验值吻合良好, 验证了所采用计算方法、网格分块策略和边界条件处理方法的正确性.Abstract: The flow-fields around powered isolated turbofan engine model and powered DLR-F6 wing/body/pylon/nacelle(WBPN) model were numerically simulated and analyzed by the appropriate fan inlet face and jet-exit boundary conditions.Three-dimensional time-dependent compressible Reynolds-averaged Navier-Stokes equations were solved with third-order upwind-biased flux-difference splitting method and approximate factorization method.The point-to-point patched multi-block technology was used to generate high quality grid.The multi-grid technique was employed to accelerate the convergence.For a better simulation of the powered effects, the fan inlet face boundary conditions and jet-exit boundary conditions were determined.Computational results and comparisons with experimental data were presented.The good agreement indicates that the numerical method, grid blocking strategy and management of boundary conditions are validated.
点击查看大图
计量
- 文章访问数: 1747
- HTML浏览量: 2
- PDF量: 500
- 被引次数: 0