Investigation of the YF-16 in High Angle of Attack Asymmetric Flight.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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A study was made of the theoretical departure modes of the YF-16 due to pitch and yaw perturbations from asymmetrical rectilinear flight. An alpha-beta control boundary was developed, and within that boundary perturbations of 20 degsec and 30 degsec were introduced. The areas of uncontrolled motions were mapped out and the motions were categorized. Three types of motions were identified erect spins, inverted spins, and rolling departures. For yaw perturbations only, a simple controller was modelled which had as its inputs alpha, beta, and yaw rate. The controller prevented the aircraft from departing controlled flight. Time traces of the various departure modes and the effects of including a departure controller are presented in the appendices. Author
- Attack and Fighter Aircraft