Effects of Pitch Angles of Attack on Center of Pressure in the Yaw Plane for Small Sideslip Angles at mach Number

摘要

This memorandum supplements A-3B Aerodynamic data memo. #14C by presenting test values at Mach number 1.25. The test values show the effect of large angles of attack in pitch combined with small sideslip angles on center of pressure in the yaw plane.