WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEEDS OF A SPOILER-SLOT- DEFLECTOR COMBINATION ON A NACA 65A006 WING WITH QUARTER-CHORD LINE SWEPT BACK 32.6
Wind-tunnel investigation of a spoiler-slot-deflector combination on a swept NACA 65A006 wing at high subsonic speeds, documenting aerodynamic force and moment data.
About This Book
This technical report presents wind-tunnel data for a spoiler-slot-deflector combination installed on a NACA 65A006 wing with the quarter-chord line swept back 32.6 degrees.
Tests were conducted at high subsonic speeds to examine the aerodynamic characteristics of the control configuration.
The study provides measured force and moment coefficients for a range of spoiler and deflector deflections.
Results contribute to the understanding of control effectiveness on swept wings operating near transonic conditions.
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