Wind Tunnel Investigation of a 1/6-Scale V/STOL Model (Bell X-22A). Part 2. Additional Vertical Tail and Wing Trailing Edge Modifications

摘要

A 1/6-scale unpowered model of a ducted-propeller, V/STOL aircraft (Bell X-22A) was tested in an 8by 10-foot, rectangular, atmospheric wind tunnel. During this test numerous modifications were made to the initial configuration selected during phase I investigation. Most of these modifications involved detail changes of the vertical tail in order to develop satisfactory aerodynamic stability characteristics. The test was restricted to the cruise regime. Data are presented in tabular form as aerodynamic coefficients in the stability axes system and in the body axes system. (Author)