Abstract
Small amplitude angular perturbations, of the order of one-half degree, can substantially modify the flow structure along a three-dimensional wing configuration, which is quantitatively characterized using a technique of high-image-density particle image velocimetry. Excitation at either the fundamental or the first subharmonic of the spanwise-averaged instability frequency of the separating shear layer from the stationary wing nearly eliminates the large-scale separation zone along the wing at high angle of attack. The physics of the flow is interpreted in terms of time-mean streamlines, vorticity and Reynolds stress, in conjunction with phase-averaged patterns of instantaneous vorticity. Distinctive vorticity patterns occur along the leading edge when the time-averaged separation zone is minimized.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
Bruce RJ (2003) Low speed wind tunnel tests on the 1303 UCAV concept. Technical Report TR025502, QinetiQ Ltd
Gordnier DV, Visbal MR (1998) Higher-order schemes for Navier-Stokes equations: Algorithms and implementation into FDl3DI. Technical Report AFRL-VA-WP-TR-1998-3060, Air Vehicles Directorate, Air Force Research Laboratory
Gordnier RE, Visbal MR (2005) Compact difference scheme applied to simulation of low-sweep delta wing flow. AIAA J 43:1744–1752
Gordnier RE, Visbal MR (2006) High-order simulation of low sweep delta wing flows using ILES and hybrid RANS/ILES models. AIAA Paper 2006-0504
Gordnier RE, Visbal MR, Gursul I, Wang Z (2007) Computational and experimental investigation of a nonslender delta wing. AIAA Paper 2097-0894
Gursul I (2004a) Recent developments in delta wing aerodynamics. Invited Review Article, The Aeronautical Journal, pp 437–452
Gursul I (2004b) Vortex flows on UAVs: issues and challenges. Aeronautical J 108:597–610
Gursul I, Gordnier R, Visbal M (2005) Unsteady aerodynamics of nonslender delta wings. Prog Aerospace Sci 41:515–557
Gursul I, Vardaki E, Wang Z (2006) Active and passive control of reattachment on various low-sweep wings. AIAA Paper 2006-506
Ho C-M, Huerre P (1984) Perturbed free shear layers. Ann Rev Fluid Mech 16:365–422
Kosoglu MA (2007) Flow structure along a 1303 unmanned combat air vehicle. PhD Dissertation, Lehigh University, Bethlehem, PA
McParlin SC, Bruce RJ, Hepworth AG, Rae AJ (2003) Low speed wind tunnel tests on the 1303 UCAV concept. QinetiQ/fST/tR025502/1.0, QinetiQ, Ltd., Farnborough, UK
Michalke A (1964) On the inviscid instability of the hyperbolic tangent velocity profile. J Fluid Mech 19:543–556
Nelson RC, Corke TC, He C, Othman H, Matsuno T (2007) Modification of the flow structure over a UAV wing for roll control. AIAA Paper 2007-884
Ol MV (2006) Water tunnel velocimetry results for the 1303 UCAV configuration. AIAA Paper 2006-2990
Ol MV, Gharib M (2003) Leading-edge vortex structure of nonslender delta wings at low Reynolds number. AIAA J 41:16–26
Petterson K (2006) CFD analysis of the low-speed aerodynamic characteristics of a UCAV. AIAA Paper 2006-1259
Sherer SE, Gordnier RE, Visbal MR (2008) Computational study of a UCAV configuration using a high-order overset-grid algorithm. AIAA Paper 2008-626
Taylor G, Wang Z, Vardaki E, Gursul I (2007) Lift enhancement over flexible non-slender delta wings. AIAA J 45(12):2979–2993
Vardaki E, Wang Z, Gursul I (2008) Flow reattachment and vortex reformation on oscillating low-aspect-ratio wings. AIAA J 46(6):1453–1462
Visbal MR (2009) High-fidelity simulation of transitional flows past a plunging airfoil. AIAA Paper 2009-391
Wong MD, Flores J (2006) Application of OVERFLOW-MLP to the analysis of the 1303 UCAV. AIAA Paper 2006-2987
Wong MD, McKenzie GJ, Ol MV, Petterson K, Zhang S (2006) Joint TTCP CFD studies into the 1303 UCAV performance: first year results. AIAA Paper 2006-2984
Yaniktepe B, Rockwell D (2004) Flow structure on a delta wing of low sweep angle. AIAA J 42:513–523
Yaniktepe B, Rockwell D (2005) Flow structure on diamond and lambda planforms: trailing-edge region. AIAA J 43:1490–1512
Yavuz MM, Elkhoury M, Rockwell D (2004) Near-surface topology and flow structure on a delta wing. AIAA J 42:332–340
Zhang F, Khalid M, Ball N (2005) A CFD based study of UCAV 1303 model. AIAA Paper 2006-4615
Acknowledgments
The authors gratefully acknowledge the support of the Air Force Office of Scientific Research under grants monitored by Lt. Col. Rhett Jefferies and Dr. John Schmisseur.
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
About this article
Cite this article
Yilmaz, T.O., Rockwell, D. Flow structure on a three-dimensional wing subjected to small amplitude perturbations. Exp Fluids 47, 579–597 (2009). https://doi.org/10.1007/s00348-009-0637-2
Received:
Revised:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s00348-009-0637-2