北京航空航天大学学报 ›› 2014, Vol. 40 ›› Issue (4): 551-557.doi: 10.13700/j.bh.1001-5965.2013.0291

• 论文 • 上一篇    下一篇

斜置飞翼超声速旅客机气动外形参数选取方法

胡姝瑶, 蒋崇文, 高振勋, 李椿萱   

  1. 北京航空航天大学 国家计算流体力学实验室, 北京 100191
  • 收稿日期:2013-05-24 出版日期:2014-04-20 发布日期:2014-05-07

Oblique flying wing supersonic airliner aerodynamic configuration parameters selection method

Hu Shuyao, Jiang Chongwen, Gao Zhenxun, Lee Chunhian   

  1. National Laboratory for Computational Fluid Dynamics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2013-05-24 Online:2014-04-20 Published:2014-05-07

摘要: 提出根据载客量、航程、巡航速度和高度即可初步确定斜置飞翼超声速旅客机气动外形参数的方法.讨论了对称面弦长的选取范围,确定了展弦比、起飞翼载荷与展长的关系,提出了展弦比、起飞翼载荷的选取原则,并推导了油箱展向长度和客舱展向长度迭代公式.为了研究技术要求对斜置飞翼超声速旅客机气动外形参数的影响,对载客量250~550、航程6500~10000 km、升阻比11~12内若干设计点进行了研究分析.结果表明,所设计的飞翼存在一起飞重量阈值,当起飞重量小于该阈值时机翼面积由展弦比下限确定,当起飞重量大于此阈值时机翼面积由起飞翼载荷上限确定;提高巡航升阻比可减小由起飞翼载荷上限确定的机翼面积.

Abstract: The method is capable of providing the basic geometry of the flying wing simply by given certain bulk parameters, such as the passenger number, range, cruise velocity and height. Discussions were paid to the selection of the appropriate symmetry plane chord, the constraint of the wing span caused by the aspect ratio and take-off wing loading, the range identification of the aspect ratio and take-off wing loading, as well as the dimension derivations of the fuel tank and passenger cabin. In order to demonstrate the correlation between configuration parameters and design demands, several designed points were calculated using the present method under the conditions of 250-550 passengers and 6 500-10 000 km flight range, with lift-to-drag ratio of 11-12. The results yield that there exists a take-off weight threshold of the designed wing. When the take-off weight is less than the threshold value, minimum aspect ratio defines the wing area; whereas the take-off weight is larger than the value, maximum wing loading determines the wing area. Improvements on the cruise lift-to-drag ratio would lessen the wing area which can be decided by the maximum wing loading.

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