LOW-SPEED WIND-TUNNEL INVESTIGATION OF FLIGHT SPOILERS AS TRAILING-VORTEX-ALLEVIATION DEVICES ON A MEDIUM-RANGE WIDE-BODY TRI-JET AIRPLANE MODEL

摘要

An investigation was made in the Langley V/STOL tunnel to determine, by the trailing wing sensor technique, the effectiveness of various segments of the exist¬ing flight spoilers on a medium-range wide-body tri-jet transport airplane model when they were deflected as trailing-vortex-alleviation devices. The four combina¬tions of flight-spoiler segments investigated were effective in reducing the induced rolling moment on the trailing wing model by as much as 15 to 60 percent at distances behind the transport model of from 3.9 to 19.6 transport wing spans, 19.6 spans being the downstream limit of distances used in this investigation. Essentially all of the reduction in induced rolling moment on the trailing wing model was realized at a spoiler deflection of about 45°.