Flight and wind-tunnel comparisons of the inlet-airframe interaction of the F-15 airplane
Flight and wind-tunnel comparisons of the inlet-airframe interaction of the F-15 airplane
复制标题
F-15 飞机进气道与机身相互作用的飞行和风洞比较
DOI：
10.2514/6.1979-102
复制
发表时间：
1984
期刊：
影响因子：
--
通讯作者：
S. Whitmore
中科院分区：
文献类型：
--
作者：
L. D. Webb;D. Andriyich;S. Whitmore
本文讨论了进气和喷管的设计及其与飞机的相互作用，它们可能占现代高性能飞机总阻力的很大比例。描述了进气道/机体相互作用程序和进行的飞行试验。将7.5%风洞模型的进气阻力和升力数据与配备了与模型匹配的仪器的F-15飞机的数据进行了比较。给出了在马赫数分别为0.6、0.9、1.2和1.5的情况下，压力系数随不同的整流角、捕集比、流动干扰和迎角的变化。
The design of inlets and nozzles and their interactions with the airplane which may account for a large percentage of the total drag of modern high performance aircraft is discussed. The inlet/airframe interactions program and the flight tests conducted is described. Inlet drag and lift data from a 7.5% wind-tunnel model are compared with data from an F-15 airplane with instrumentation to match the model. Pressure coefficient variations with variable cowl angles, capture ratios, examples of flow interactions and angles of attack are for Mach numbers of 0.6, 0.9, 1.2, and 1.5 are presented.