水陆两栖飞机内吹式襟翼优化设计
收稿日期: 2015-09-09
修回日期: 2015-11-17
网络出版日期: 2016-02-19
Optimization design of an internal blown flap used in large amphibian
Received date: 2015-09-09
Revised date: 2015-11-17
Online published: 2016-02-19
为改善某型水陆两栖飞机的起降性能,提高其抗浪能力,需设计高性能吹气襟翼以满足其性能要求。本文在国内外已有的吹气襟翼研究基础上,结合飞机气动综合优化设计框架及计算流体力学(CFD)的优势,以设计出高气动效率及工程实用性的内吹式襟翼方案作为设计目标,对内吹式襟翼的基本形式、吹气缝道位置及喷缝参数等进行综合优化设计,最终通过风洞试验来验证优化设计方案的有效性。从分析及验证结果来看,通过本优化设计方法所设计的内吹式襟翼,能在使用相同吹气动量系数的条件下,明显推迟襟翼上的气流分离,实现最大升力系数20%左右的提升,显著提升了内吹式襟翼的气动效率,为进一步实现内吹式襟翼的工程应用奠定了基础。
王妙香 , 孙卫平 , 秦何军 . 水陆两栖飞机内吹式襟翼优化设计[J]. 航空学报, 2016 , 37(1) : 300 -309 . DOI: 10.7527/S1000-6893.2015.0310
In order to improve the aerodynamics performance and increase the seaworthiness of an amphibian aircraft,the blown flap with high performance is designed to meet the requirements.Based on experiences about blown flap domestic and overseas,combined with the aircraft design framework of the aerodynamic integrated optimization and the advantage of the Computational Fluid Dynamics(CFD),it is intended to design a scheme with high aerodynamic efficiency and practicality in engineering.The form of internal blown flap,the location of blow gaps and the parameters of gaps are designed;the efficiency of the scheme is certified by wind tunnel tests.These results show that the internal blown flap designed by the optimization method obviously delays flow separation of the flap,and maximum lift coefficient increases 20% compared with basic configuration under the same momentum coefficient condition,and the aerodynamic efficiency of blown flap is increased significantly,and the seaworthiness of the amphibian aircraft is raised.It is believed that the obtained results perhaps could be of some value in the engineering application of internal blown flap.
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