Numerical Prediction of Dynamic Derivatives Based on Computational Fluid Dynamics
First, an unsteady CFD method is established for simulating fluid with moving boundary, based on unstructured deforming mesh technology. A MUSCL type cell-centered finite-volume scheme is presented for solving the 2-D and 3-D time-dependent Euler equations. Solutions are advanced in time by explicit three-stage Runge-Kutta integration with up to second-order temporal accuracy. To avoid grid motion induced error, the geometric conservation law (GCL) is satisfied numerically. These methods are validated to simulate unsteady transonic flows about an oscillating airfoil (2D) and an oscillating rigid rectangular wing (3D). Computational results are in good agreement with the experimental data. Secondly, a fast numerical method based on Newtons theory of collision is performed. In fact, it is useful and efficient to describe pressure on an aircrafts surface in supersonic flow. Lastly, these numerical methods are all developed to be used for computing dynamic derivatives. As a benchmark, dynamic derivatives of a supersonic missile are computed using numerical methods which are performed in this paper. The results of unsteady CFD and fast numerical method are all in good agreement with the experimental data of wind tunnel tests. Numerical methods in this paper include an unsteady CFD method and a fast numerical method based on Newtons theory of collision have been validated and can be used to study stability and control characteristic of aircraft by predicting dynamic derivatives efficiently.
Cartesian grid dynamic grids dynamic derivative numerical simulation
Zhang Yudong Zhang Shaoping Wei Ran
Aerodynamics research and development center, China academy of aerospace aerodynamics,Beijing 100074 Aerodynamics research and development center,China academy of aerospace aerodynamics,Beijing 100074,
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
448-451
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）