METHOD OF MINIMIZING THE ATTITUDE HUMP PHENOMENON AND A ROTARY WING AIRCRAFT PROVIDED WITH STABILIZER MEANS THEREFOR

摘要

A method of minimizing the attitude hump phenomenon relating to a rotary wing aircraft (1) having an airframe (2) extending longitudinally from a front end (3) to a rear end (4) together with upper pitching-stabilizer means (10) and at least one lower pitching-stabilizer means (20). Under such circumstances, each lower stabilizer means (20) is placed in a wake (8) from said upper stabilizer means (10) as generated by a stream of air (7) passing through said rotary wing (5) and impacting against the upper surface (10′) of an upper stabilizer means (10).