Dye Visualization of the Vortical Flow Structure over a Double-Delta Wing
Publication: Journal of Aerospace Engineering
Volume 25, Issue 4
Abstract
An investigation of the flow field around a double-delta wing was carried out at the Aerodynamics Analysis and Design Laboratory's (AADL) water tunnel facility. The model has a sharp leading edge and 76/40° configuration, which is representative of current fighter aircraft. The experiments were conducted at Reynolds numbers of 10,000 and 15,000. The dye injection technique was utilized to analyze the flow. A comparison of the vortical flow structure and the bursting point locations was done for a Reynolds number of 15,000 and found to be in reasonable agreement. The major objective of this experiment was to study the effect of the angle of attack (AOA) and Reynolds number on the vortical flow structure. In this flow visualization result, the dominant feature of the AOA and Reynolds number effect on the vortical flow structure over the double-delta wing has been observed. With increasing Reynolds number, the distance between the vortex trajectory and the model surface becomes smaller. As the AOA increases, the intertwining or coiling up features cannot be seen and the vortex bursting point locations move upstream. The distance between the vortical streakline and the model surface becomes larger with increasing AOA. The crossover point of the main and strake wing vortices also depends on the AOA.
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Acknowledgments
This research was supported by the National Space Laboratory (NSL) program through the National Research Foundation of Korea funded by the Ministry of Education, Science and Technology (Grant No. 2011-0020837), and the Agency for Defense Development and FVRC under Contract UD100048JD and Grant No. 2011-A423-0063 (Unsteady Combustion Dynamics and Combustion Instability).
References
Brennenstuhl, U. (1985). “Experimentelle und theoretische untersuchungen uber die wirbelbildung an doppeldeltaflugeln.” Ph.D. dissertation, Carola Wilhelmina Technical Univ., Braunschweig, Germany.
Cunningham, A. M., Jr., and den Boer, R. G. (1990). “Low speed aerodynamics of a pitching straked wing at high incidence—Part II: Harmonic analysis.” J. Aircr., 27(1), 31–41.
Erickson, G. E. (1980). “Flow studies of slender wing vortices.” 13th Fluid and Plasma Dynamics Conf., American Institute of Aeronautics and Astronautics, Washington, DC.
Frink, N. T., and Lamar, J. E. (1980). “Water-tunnel and analytical investigation of the effect of strake design variables on strake vortex breakdown characteristics.” NASA TP 1676, National Aeronautics and Space Administration, Washington, DC.
Gai, S. L., Roberts, M., Barker, A., Kleczaj, C., and Riley, A. J. (2004). “Vortex interaction and breakdown over double-delta wings.” Aeronaut. J., 108(1079), 27–34.
Graves, T. V., Nelson, R. C., Schwimely, S. L., and Ely, W. L. (1992). “Aerodynamic performance of strake wing configurations.” NASA High-Angle-of-Attack Technology Conf., National Aeronautics and Space Administration, Washington, DC, 173–204.
Hebbar, S. K., Platzer, M. F., and Alkhozam, A. M. (1996). “Experimental study of vortex flow control on double-delta wings using fillets.” J. Aircr., 33(4), 743–751.
Hebbar, S. K., Platzer, M. F., and Chand, W.-H. (1997). “Control of high-incidence vortical flow on double-delta wings undergoing sideslip.” J Aircr., 34(4), 506–513.
Hebbar S. K., Platzer, M. F., and Fritzelas, A. E. (2000). “Reynolds number effects on the vortical-flow structure generated by a double-delta wing.” Exp. Fluids, 28(3), 206–216.
Hebbar, S. K., Platzer, M. F., and Li, F. H. (1993). “A visualization study of the vortical flow over a double-delta wing in dynamic motion.” 11th Computational Fluid Dynamics Conf., American Institute of Aeronautics and Astronautics, Washington, DC.
Kern, S. B. (1993). “Vortex flow control using fillets on a double-delta wing.” J Aircr., 30(6), 818–825.
Lamar, J. E., and Frink, N. T. (1981). “Experimental and analytical study of the longitudinal aerodynamic characteristics of analytically and empirically designed strake-wing configurations at subcritical speeds.” NASA TP 1803, National Aeronautics and Space Administration, Washington, DC.
Olsen, P., and Nelson, R. (1989). “Vortex interaction over double-delta wings at high angles of attack.” 7th AIAA Applied Aerodynamics Conf., American Institute of Aeronautics and Astronautics, Washington, DC, 238–248.
Sohn, M. H, Lee, K. Y., and Chang, J. W. (2008). “Delta-wing vortex visualization using micro-sized water droplets generated by an ultrasonic humidifier.” J. Visualization, 11(4), 337–346.
Verhaagen, N. G. (1995). “A study of the vortex flow over a 76/40 double-delta wing.” NASA ICASE Report.No.95-5, National Aeronautics and Space Administration, Washington, DC, 173–204.
Verhaagen, N. G. (1998). “Tunnel wall effect on the flow around a 76/40 double-delta wing.” 36th Aerospace Sciences Meeting and Exhibit, American Institute of Aeronautics and Astronautics, Washington, DC.
Information & Authors
Information
Published In
Journal of Aerospace Engineering
Volume 25 • Issue 4 • October 2012
Pages: 541 - 546
Copyright
© 2012 American Society of Civil Engineers.
History
Received: Jan 28, 2011
Accepted: Dec 14, 2011
Published online: Dec 17, 2011
Published in print: Oct 1, 2012
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