发明名称 |
Aircraft boundary layer control system with discharge transpiration panel |
摘要 |
An improvement to boundary layer control system, including a transpiration panel (58) for transpiring suction air in a distributed manner, is provided. The transpiration panel (58) replaces the discharge nozzle of prior art flow control systems. The transpiration panel (58) is generally a rigid panel having a plurality of small holes (62) extending from an inner panel surface (56) to a smooth outer panel surface (54). The transpiration panel (58) is positioned flush with an external aircraft surface in a region where laminar flow control is not being attempted. Exemplary subsonic and supersonic boundary layer control systems including the transpiration panel (58) are provided. A preferred location of the transpiration panel (58) for the subsonic application is the underside of a wing (80), near the leading edge. A preferred location of the transpiration panel (58) for the supersonic application including on the upper surface of a wing (114) near the fuselage (118), in a turbulent wedge region.
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申请公布号 |
US5772156(A) |
申请公布日期 |
1998.06.30 |
申请号 |
US19950566584 |
申请日期 |
1995.11.30 |
申请人 |
THE BOEING COMPANY |
发明人 |
PARIKH, PRADIP G.;NEUMANN, FRANK D. |
分类号 |
B64C21/02;(IPC1-7):B64C21/06 |
主分类号 |
B64C21/02 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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