Abstract : This report describes the Phase 2 portion of a joint U.S. Air Force U.S. Navy sponsored investigation of innovative aerodynamic control concepts for fighter aircraft without vertical tails. The Phase 1 work consisted of effector performance prediction, vehicle integration assessment, and transition studies for numerous control effector concepts. The Phase 2 effort is an extension of the Phase 1 work and consists mainly of three wind tunnel tests to acquire more information about the aerodynamic performance of all moving wing tips (AMTs) and spoiler slot deflectors (SSDs). These tests clearly showed both the AMT and SSD can produce significant yaw control power and are strong control effector candidates for tailless fighters. Predicted vehicle dynamics from Phase 1 are compared with predictions developed utilizing the new aerodynamic data acquired in Phase 2.