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 memorandum #14C by presenting the effect of angle of attack in pitch on center of pressure on the yaw plane for small angles of sideslip at an additional Mach number, namely M=4.5. Memorandum #14C gives similar results at M=2.47 and 3.80.