Commenced in January 2007
Frequency: Monthly
Edition: International
Paper Count: 32127
Investigations of Free-to-Roll Motions and its Active Control under Pitch-up Maneuvers

Authors: Tanveer A. Khan, Xue Y. Deng, Yan K. Wang, Xu Si-Wen


Experiments have been carried out at sub-critical Reynolds number to investigate free-to-roll motions induced by forebody and/or wings complex flow on a 30° swept back nonslender wings-slender body-model for static and dynamic (pitch-up) cases. For the dynamic (pitch-up) case it has been observed that roll amplitude decreases and lag increases with increase in pitching speed. Decrease in roll amplitude with increase in pitch rate is attributed to low disturbing rolling moment due to weaker interaction between forebody and wing flow components. Asymmetric forebody vortices dominate and control the roll motion of the model in dynamic case when non-dimensional pitch rate ≥ 1x10-2. Effectiveness of the active control scheme utilizing rotating nose with artificial tip perturbation is observed to be low in the angle of attack region where the complex flow over the wings has contributions from both forebody and wings.

Keywords: Artificial Tip Perturbation, ExperimentalInvestigations, Forebody Asymmetric Vortices, Non-slender Wings-Body Model, Wing Rock

Digital Object Identifier (DOI):

Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 1385


[1] J. Katz, "Wing / vortex interactions and wing rock". Progress in aerospace sciences 35 (1999); 727-750.
[2] R. C. Nelson, & A. Pelletier, "The unsteady aerodynamics of slender wings and aircraft undergoing large amplitude maneuvers". Progress in Aerospace Sci. 39(2003), 185-248.
[3] J. M. Brandon, and L. T. Nguyen, "Experimental study of effects of forebody geometry on high angle of attack stability". J Aircraft 1988: 25(7):591-7.
[4] T. Quast, R. C. Nelson, & D. F. Fisher. "A study of high alpha dynamic and flow visualization for 2.5% model of the F-18 HARV undergoing wing rock". AIAA Paper 91-3267.
[5] D. L. Williams II, R. C. Nelson, & D. F. Fisher. "An investigation of the X-31 roll characteristics at high angle-of-attack through subscale model testing". AIAA paper 94-0806.
[6] B. N. Pamadi, D. M. Rao, & T. Niranjana, "Wing rock and roll attractor of delta wings at high angles of attack". AIAA Paper 94-080.
[7] D. L. Williams II, R. C. Nelson. & L. E. Ericsson, "Influence of wing separation on forebody induced/driven rock". AIAA paper 95-3441-CP.
[8] T. T. Ng, C. J. Saurez, B. R. Kramer, L. Y. Ong, B. Ayers & G. N. Malcolm, "Forebody vortex control for wing rock suppression". J. Aircraft, 31, 298-305.
[9] X. Y. Deng, G. Wang, X. R. Chen, Y. K. Wang, P. Q. Liu, "Influence of nose perturbations on behaviors of asymmetric vortices over slender body". AIAA paper 2002-4710.
[10] X. Y. Deng, G. Wang, X. R. Chen, Y. K. Wang, P. Q. Liu, & Z. X. Xi, "A Physical model of asymmetric vortices flow structure in regular state over slender body at high angle of attack". Science in China (series E), 2003, 46(6): 561-573.
[11] J. Zhang, "Research on control method and mechanism of forebody vortices induced wing rock". Masters Dissertation (in Chinese), School of Aeronautical Science & Engineering, Beihang University, Beijing China, July 2010.
[12] I. Gursul, R. Gordnier, M. Visbal, "Unsteady aerodynamics of nonslender delta wings". Progress in Aerospace Sciences 41 (2005) 515- 557.
[13] B. Yaniktepe, D. Rockwell, " Flow structure on a delta wing of low sweep angle". AIAA J 2004;42(3):513-23.
[14] G. Taylor, I. Gursul, "Buffeting flows over a low sweep delta wing". AIAA J 2004; 42(9):1737-45.
[15] S. C. Yen, L. C. Huang, "Flow patterns and aerodynamic performance of un-swept and swept-back wings". J. Fluids Engineering, Nov 2009, vol. 131, 111101-1-10.
[16] G. Wang, X. Y. Deng, Y.K. Wang, X. R. Chen," Zonal study of flow patterns around an ogive-cylinder at subcritical Re." J. Experiments and Measurements in Fluid Mechanics, 17(2): 19-36 (in Chinese), 2003.
[17] L. E. Ericsson, "Analysis of the Effect of Sideslip on Delta Wing Roll- Trim Characteristics", J. of Aircraft, 1997, 34 (5): 585 - 591.
[18] L. E. Nguyen, L. P. Yip, J. R. Chamber, "Self-induced wing rock of slender delta wings". AIAA Paper 81-1883