1. was an analytical study to identify many promising 2-0 nozzle concepts and their potential payoffs. The second program, Reference 2, was an experimental program involving wind tunnel testing of five low aspect ratio 2-D nozzles on a NASA model with B simple aerodynamic shape. Two engine companies, General Electric (GE) and Pratt and Whitney Aircraft (PSWA), were major participants in these programs.
2. The mission and flight performance requirements established for the ATS vehicle are summarized in Figure 3. This is a long range, high altitude supersonic strike mission, the dominant features being a 350 nautical mile leg a t Mach 0.9 and a 200 nautical m i l e leg a t Mach 2.0. The prime objective is to deliver two, 2000 Ib weapons from stand-of f range. The maneuverability requirement is for self-defense. A sustained normal load Eactor requirement of 3 g's was established a t Mach 0.9/30,000 f t , maximum power t o meet this goal.
3. OPllDaell Fig. 1 ANC4 Study Configurations
4. A l l the multifunction nozzles incorporated dry power thrust reversing (TR) for both inflight and landing and all the 2-0 nozzles also incorporated thrust vectoring (TV) in the pitch plane of 2 30" from horizontal. The vectoring l i m i t for the multifunction axisymmetric nozzle was 2 20" due to mechanical limitations.