There is no abstract available for this article.
The advanced combat aircraft configuration model was made and corresponding wind tunnel tests were conducted by AVIC Aerodynamics Research Institute. The authors thank their great contributions to this work.
Appendixes A and B.
[1] Wang Q, Qian W Q, Ding D. A review of unsteady aerodynamic modeling of aircrafts at high angles of attack. Acta Aeronautica et Astronautica Sinica, 2016, 37: 2331--2347. Google Scholar
[2] Murphy P C, Klein V, Nathan M S. Progressive aerodynamic model identification from dynamic water tunnel test of the F-16XL aircraft. In: Proceedings of AIAA Atmospheric Flight Mechanics Conference and Exhibit, Providence, 2004. AIAA 2004-5277. Google Scholar
[3] Luchtenburg D M, Rowley C W, Lohry M W. Unsteady High-Angle-of-Attack Aerodynamic Models of a Generic Jet Transport. J Aircraft, 2015, 52: 890-895 CrossRef Google Scholar
[4] Abramov N, Goman M, Khrabrov A. Aircraft dynamics at high incidence flight with account of unsteady aerodynamic effects. In: Proceedings of AIAA Atmospheric Flight Mechanics Conference and Exhibit, Providence, 2004. AIAA 2004-5274. Google Scholar
[5] Ignatyev D I, Khrabrov A N. Neural network modeling of unsteady aerodynamic characteristics at high angles of attack. Aerospace Sci Tech, 2015, 41: 106-115 CrossRef Google Scholar
[6] Wang Q, Qian W, He K. Unsteady aerodynamic modeling at high angles of attack using support vector machines. Chin J Aeronautics, 2015, 28: 659-668 CrossRef Google Scholar
[7] Klein V, Morelli E A. Aircraft System Identification: Theory and Practice. Reston: American Institute of Aeronautics and Astronautics, Inc., 2006. 191--194. Google Scholar
[8] Murphy P C, Klein V, Frink N T, et al. System identification applied to dynamic CFD simulation and wind tunnel data. In: Proceedings of AIAA Atmospheric Flight Mechanics Conference, Portland, 2011. AIAA 2011-6522. Google Scholar
Figure 1
(Color online) Pitching forced oscillation tests in wind tunnel.