格尼襟翼在冰风洞混合翼设计中的应用

doi:10.7527/S1000-6893.2018.22387

流体力学与飞行力学

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格尼襟翼在冰风洞混合翼设计中的应用

韩志熔, 赵克良, 颜巍

中国商飞上海飞机设计研究院, 上海 201210

出版日期:2019-02-15 发布日期:2018-09-19
通讯作者: 韩志熔 E-mail:hanzhirong@comac.cc

Application of Gurney flap in hybrid-wing design for icing wind tunnel

HAN Zhirong, ZHAO Keliang, YAN Wei

COMAC Shanghai Aircraft Design and Research Institute, Shanghai 201210, China

Online:2019-02-15 Published:2018-09-19

摘要/Abstract

摘要： 提出面向工程、面向适航的混合翼设计准则，基于此准则提出将格尼襟翼应用于民机机翼结冰风洞试验的单段混合翼设计中。设计准则中只对驻点位置和前缘吸力峰值提出保守性要求，易于工程实现，满足结冰适航要求。对于偏离设计点较大的状态，在单段混合翼后缘添加格尼襟翼并配合迎角调整，使得单段混合翼在此状态点处仍满足设计准则。这样使得单段混合翼也能应用于试验状态比较广的结冰风洞试验中。格尼襟翼的使用，降低了混合翼设计、试验费用，为民机结冰试航取证节约了时间。

关键词: 面向适航, 混合翼设计准则, 格尼襟翼, 驻点位置, 前缘吸力峰值

Abstract: A project-and airworthiness-oriented hybrid-wing design criterion is presented. Based on the criterion, the Gurney flap is applied to the single hybrid-wing design in the icing tunnel test. The criterion only postulates conservative requirements for the location of stagnation point and the value of suction peak, easing the project realization and meeting airworthiness requirements. For the states deviating largely from the design point, the single hybrid-wing can still meet the criterion by adding the Gurney flap and adjusting the angle of attack, making the single hybrid-wing applicable to the icing tunnel test with a wide range of states. The use of the Gurney flap reduces the costs of designing and testing, saving time for the icing airworthiness of civil aircraft.

Key words: airworthiness-oriented, hybrid-wing design criterion, Gurney flap, location of stagnation point, value of suction peak

中图分类号:

V211.3

韩志熔, 赵克良, 颜巍. 格尼襟翼在冰风洞混合翼设计中的应用[J]. 航空学报, 2019, 40(2): 522387-522387.

HAN Zhirong, ZHAO Keliang, YAN Wei. Application of Gurney flap in hybrid-wing design for icing wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(2): 522387-522387.

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格尼襟翼在冰风洞混合翼设计中的应用

Application of Gurney flap in hybrid-wing design for icing wind tunnel

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