ROCKET-MODEL INVESTIGATION OF THE ROLLING EFFECTIVENESS OF A FIGHTER-TYPE WING-CONTROL CONFIGURATION AT MACH NUMBERS FROM 0.6 TO 1.5

摘要

An investigation of the rolling effectiveness of spoiler and aileron aerodynamic controls on a fighter-type airplane has been conducted at Mach numbers from 0.6 to 1.5 by the Langley Pilotleas Aircraft Research Division by utilizing rocket-propelled test vehicles.nNo effects of mutual interference between the misspend spoiler and the outboard aileron were detectable. Above the speed of sound, the ailerons were relatively ineffective as compared, with the spoiler because of wing twisting. For conditions of equal rolling effectiveness, the twisting-moment coefficient of the aileron was approximately three times that of the spoiler.