Each wing trailing edge had 2 flaperons.[^1] The flaperons would automatically droop down as speed was reduced.[^1] These flaperons could be differentially deflected and used as a speed brake.[^1] Due to the thinness of the wing 4 small actuators were used for each control surface.[^1]
The canted elevons were used for pitch control and differential elevon deflection was used for yaw control.[^1] The upward cant brought them out of the wing slipstream and allowed them to be effective at high AOA.[^1] The elevon actuators had two actuators each, each of which have dual chambers.[^1] This allowed fast movements with only one chamber, or strong movements and stiffness, with both cambers.[^1] The tail surfaces were almost 25% of the wing area.[^2]
Sources
- [1] Western Museum of Flight, Your Private Tour with Roy Martin – Episode 8Â YF-23 Flying Qualities, (Aug. 11, 2020). Accessed: Aug. 05, 2024. [Online Video]. Available: https://www.youtube.com/watch?v=aNFYdMkc09I
- [2] PeninsulaSrsVideos, YF-23 Walk Around and Design Features by Test Pilot Paul Metz, (Sep. 06, 2015). Accessed: Aug. 18, 2024. [Online Video]. Available: https://www.youtube.com/watch?v=iU8gWgz9n4U
Backlinks
[[B-1 Wing]]
[[Disadvantage of Elevons]]
F-22 Flight Control System
[[Flaperons]]
[[YF-23]]
[[YF-23 Vehicle Management System]]