• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>48th Israel Annual Conference on Aerospace Sciences 2008 >AERODYNAMIC DESIGN OF DOUBLE-SLOTTED FOWLER FLAP FOR ACROBATIC AIRCRAFT JAVELIN
【24h】

AERODYNAMIC DESIGN OF DOUBLE-SLOTTED FOWLER FLAP FOR ACROBATIC AIRCRAFT JAVELIN

机译：特技飞机贾夫林双缝式襟翼气动设计

获取原文
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

This paper presents the design of the double-slotted Fowler flap that was designed for the Javelin aircraft. The Javelin is a high-speed acrobatic aircraft, which was originally designed for leisure by Aviation Technology Group, Inc - ATG, and later on converted to a basic pilot trainer in partnership with the Israel Aerospace Industries LTD. The design of the double-slotted Fowler flap was part of the effort to decrease the landing speed of the aircraft - specifically the stall speed at landing to 90 knots. The achievement of target maximum lift was proven in test in the low speed wind runnel of University of Washington in Seattle. The increment to the sectional maximum lift coefficient by the designed Fowler flap is about 0.4 greater than that found in literature. The stall speed at landing (Vstall=90 knots) was achieved. The use of modern CFD codes enabled fast and efficient design of the flap, and good prediction of the maximum lift.
机译：本文介绍了专为标枪飞机设计的双缝Fowler襟翼的设计。标枪是一种高速杂技飞机，最初是由航空技术集团公司（ATG）设计用于休闲的，后来与以色列航空航天工业有限公司合作转变为基础飞行员教练机。双开槽的福勒襟翼的设计是降低飞机着陆速度的努力的一部分，特别是降落时的失速速度达到90节。在西雅图华盛顿大学的低速风道中测试证明了达到目标最大升力的效果。设计的Fowler襟翼使截面最大升力系数的增量比文献中的数值大约0.4。达到了着陆时的失速速度（Vstall = 90节）。使用现代CFD代码可以快速，高效地设计襟翼，并可以很好地预测最大升程。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号