The invention belongs to the field of an aircraft air inlet channel design, and particularly relates to a low-speed static pressure type air inlet channel suitable for a flying wing layout airplane. The air inlet channel comprises a lip and an inner pipeline. The lip is in an irregular pentagon shape and comprises a front edge (101), a left side edge (102), a right side edge (103), a left rear edge (104) and a right rear edge (105). The inner pipeline comprises an air inlet channel inlet section (1) and an air inlet channel main section (2). According to the low-speed static pressure type airinlet channel suitable for the flying wing layout airplane, by designing a novel opening surface form, a vortex aligning structure rolled up by the side edges of the lip of the air inlet channel is greatly weakened, excessive distortion and a total pressure loss of a flow field caused after vortexes are sucked into the air inlet channel are avoided, and therefore the performance of the air inlet channel is improved. And meanwhile, in order to solve the problem of difficult air intake, an adverse pressure gradient of the pipeline in the air inlet channel is reduced to the maximum extent throughthe well-designed shape of the inner pipeline so that internal separation of the air inlet channel is weakened, and the problem of difficult air intake of a static pressure type air inlet channel isrelieved.
本申请属于飞机进气道设计领域,特别涉及一种适用于飞翼布局飞机的低速静压式进气道。所述进气道包括:唇口和内管道。所述唇口呈不规则五边形,包括前缘(101)、左侧棱(102)、右侧棱(103)、左后棱(104)以及右后棱(105);所述内管道包括进气道进口段(1)以及进气道主段(2)。本申请的适用于飞翼布局飞机的低速静压式进气道,通过设计新型口面形式,大幅削弱了进气道唇口侧棱卷起的对涡结构,避免了对涡吸入进气道后导致流场过大的畸变及总压损失,从而提升了进气道性能。同时为了解决进气困难问题,通过精心设计的内管道的形状,最大限度的减小了进气道内管道逆压梯度,从而削弱了进气道内部分离,同时缓解了静压式进气道进气困难的问题。
Low-speed static pressure type air inlet channel suitable for flying wing layout airplane
一种适用于飞翼布局飞机的低速静压式进气道
2020-12-04
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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