U.S. Patent Specifications

In an aircraft including a tunnel‐shaped aerodynamic component of substantial thickness having two walls, to wit an internal one and an external one, along which two distinct gaseous streams flow respectively, the combination of a plurality of spoilers distributed along a transverse section of said component, means located inside said component for holding each of said spoilers adjustably with respect to said component, an arcuate member in the form substantially of a circular are housed in said component concentrically therewith, the ends of said member being pivoted to said component about a common axis transverse to the axis of said tunnel‐shaped component, said member being rigid with said spoiler holding means, and control means operatively connected with the central portion of said member for pivoting said member about said common axis.