Experimental Investigation of Free-to-Roll Motion of a Blunt-Nosed Slender Body Configuration
Author:
Affiliation:
1. Aircraft and Propulsion Laboratory, Ningbo Institute of Technology, Beihang University
2. Ministry-of-Education Key Laboratory of Fluid Mechanics, Beihang University
Publisher
Japan Society for Aeronautical and Space Sciences
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://www.jstage.jst.go.jp/article/tjsass/65/5/65_T-21-30/_pdf
Reference23 articles.
1. 1) Brandon, J. M. and Nguyen, L. T.: Experimental Study of Effects of Forebody Geometry on High Angle of Attack Stability, J. Aircraft, 25 (1988), pp. 591–597.
2. 2) Katz, J.: Wing/Vortex Interactions and Wing Rock, Prog. Aerosp. Sci., 35 (1999), pp. 727–750.
3. 3) Nelson, R. C. and Pelletier, A.: The Unsteady Aerodynamics of Slender Wings and Aircraft Undergoing Large Amplitude Maneuvers, Prog. Aerosp. Sci., 39 (2003), pp. 185–248.
4. 4) Degani, D., Ishay, M., and Gottlieb, O.: Fluid-structure Interaction of a Rolling Restrained Body of Revolution at High Angles of Attack, Phys. Fluids, 29 (2017), 037106.
5. 5) Fratello, D. J., Croom, M. A., and Nguyen, L. T.: Use of Updated NASA Langley Radio-controlled Drop-model Technique for High-alpha Studies of the X-29A Configuration, AIAA-87-2559, 1987.
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