| 摘要 |
The device for lift and to reduce forward resistance of aircraft consists of a converging input duct of truncated-cone-shaped or truncated-pyramid-shaped, arranged lengthwise inside the fuselage and inclined to the longitudinal axis, with the larger opening coinciding with the front fuselage contour or periphery of maximum cross-section, and reducing in bore backwards so that its generatrix or lower side coincides with the lower surface of the fuselage parallel to the aircraft's longitudinal axis and the generatrix or upper edge forms an acute angle with the aircraft's longitudinal axis. The narrowest end of the duct discharges into the input of the turbofan, UHD, etc. type drive engines which discharge through a rear outlet duct facing backwards with the rear end curved slightly downward.
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