AERODYNAMIC EFFECTS OF TRANSITION STRIP APPLICATION ON A MULDICON WING IN LOW-SPEED WIND TUNNEL TESTING
DOI:
https://doi.org/10.11113/jtse.v13.259Keywords:
MULDICON wing, Rounded leading-edge, Vortices, Flow separation, Pitching moment coefficient, Wind Tunnel (W/T) Experiments, Transition stripsAbstract
Low-sweep, blunt-leading-edge unmanned combat aerial vehicle (UCAV) configurations exhibit complex vortex separation and inconsistent aerodynamic behaviour at moderate-to-high pitch angles. This study experimentally investigates the effects of leading-edge transition strips on a lambda-planform MULDICON AVT251 wing with a 53° blunt leading-edge sweep. Wind-tunnel tests were conducted in the UTM Low-Speed Wind Tunnel at Reynolds numbers of 3.00×105 to 4.50×105 and pitch angles from −4∘ to 30∘. Lift, drag, pitching-moment coefficients, and surface flow visualisation were analysed for free-transition, 2D-transition, and 3D-transition cases. The results show that transition-strip type strongly affects the onset and progression of leading-edge vortex separation. For the 3D transition case, stall occurred at a=24∘, with CL=1.0183, while Cm remained more predictable up to a=22∘. The findings indicate that the pitching-moment coefficient is highly sensitive to flow topology and vortex-separation behaviour. Overall, the 3D transition strip is recommended to establish a repeatable baseline for future MULDICON flow-field measurements and CFD validation at subsonic.
References
Anderson, D., Graham, I., & Williams, B. (2015). Flight and motion (pp. 14–19). Routledge.
Polhamus, E. C. (1966). A concept of the vortex lift of sharp-edge delta wings based on a leading-edge-suction analogy.
Gursul, I. (2004). Recent developments in delta wing aerodynamics. The Aeronautical Journal, 108(1087), 437–452.
Rockwell, D. (1993). Three-dimensional flow structure on delta wings at high angle-of-attack—Experimental concepts and issues. In 31st Aerospace Sciences Meeting.
Visbal, M. (1995). Computational and physical aspects of vortex breakdown on delta wings. In 33rd Aerospace Sciences Meeting and Exhibit.
Gursul, I., Gordnier, R., & Visbal, M. (2005). Unsteady aerodynamics of nonslender delta wings. Progress in Aerospace Sciences, 41(7), 515–557.
Ghoreyshi, M., et al. (2016). Vortical flow prediction of a diamond wing with rounded leading edges. Aerospace Science and Technology, 57, 103–117.
Hövelmann, A., & Breitsamter, C. (2015). Leading-edge geometry effects on the vortex formation of a diamond-wing configuration. Journal of Aircraft, 52(5), 1596–1610.
Osterhuber, R. (2013). FCS requirements for future LO combat aircraft. STO/AVT-215 Workshop on Innovative Control Effectors for Military Vehicles.
Yaniktepe, B., & Rockwell, D. (2004). Flow structure on a delta wing of low sweep angle. AIAA Journal, 42(3), 513–523.
Ol, M. V., & Gharib, M. (2003). Leading-edge vortex structure of nonslender delta wings at low Reynolds number. AIAA Journal, 41(1), 16–26.
Renac, F., Barberis, D., & Molton, P. (2005). Control of vortical flow over a rounded leading-edge delta wing. AIAA Journal, 43(7), 1409–1418.
Gordnier, R., & Visbal, M. (2003). Higher-order compact difference scheme applied to low sweep delta wing flow. In 41st Aerospace Sciences Meeting and Exhibit.
Paul, M., & Rein, M. (2016). Transonic numerical and experimental investigation into unconventional lambda wing control surfaces. In 54th AIAA Aerospace Sciences Meeting.
Hummel, D. (2004). Effects of boundary layer formation on the vortical flow above slender delta wings. In Enhancement of NATO Military Flight Vehicle Performance by Management of Interacting Boundary Layer Transition and Separation.
Huri, Shabudin, & Mazuriah. (2018). Experimental investigation on blunt-edged UTM delta wing VFE-2 configurations at low Reynolds number. International Review of Mechanical Engineering (IREME), 12(3).
Loeser, T., Vicroy, D., & Schuette, A. (2010). SACCON static wind tunnel tests at DNW-NWB and 14 × 22 NASA LaRC. In 28th AIAA Applied Aerodynamics Conference.
Nangia, R., Boelens, O., & Tormalm, M. (2010). A tale of two UCAV wing designs. In 28th AIAA Applied Aerodynamics Conference.
Schuette, A., et al. (2018). Aerodynamic shaping design and vortical flow design aspects of a 53° swept flying wing configuration. In 2018 Applied Aerodynamics Conference.
Cummings, R. M., & Schütte, A. (2012). Integrated computational/experimental approach to unmanned combat air vehicle stability and control estimation. Journal of Aircraft, 49(6), 1542–1557.
Cummings, R., Schütte, A., & Hübner, A. (2013). Overview of stability and control estimation methods from NATO STO Task Group AVT-201. In 51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition.
Hitzel, S. M., et al. (2016). Vortex development on the AVT-183 diamond wing configuration—Numerical and experimental findings. Aerospace Science and Technology, 57, 90–102.
Hövelmann, A., Knoth, F., & Breitsamter, C. (2016). AVT-183 diamond wing flow field characteristics Part 1: Varying leading-edge roughness and the effects on flow separation onset. Aerospace Science and Technology, 57, 18–30.
Hövelmann, A., et al. (2016). AVT-183 diamond wing flow field characteristics Part 2: Experimental analysis of leading-edge vortex formation and progression. Aerospace Science and Technology, 57, 31–42.
Aref, P., et al. (2017). Preliminary computational aerodynamic investigation of the NATO AVT 251 multi-disciplinary configuration. In 35th AIAA Applied Aerodynamics Conference.
Kaya, H., et al. (2018). A multi-fidelity aerodynamic modelling approach for NATO AVT 251 UCAV–MULDICON. In 2018 Applied Aerodynamics Conference.
Nangia, R., et al. (2019). Aerodynamic design assessment and comparisons of the MULDICON UCAV concept. Aerospace Science and Technology, 93, 105321.
van Rooij, M., & Cummings, R. M. (2018). Aerodynamic design of an unmanned combat air vehicle in a collaborative framework. In 2018 Applied Aerodynamics Conference.
Noor, A., & Mansor, S. (2013). Measuring aerodynamic characteristics using high performance low speed wind tunnel at Universiti Teknologi Malaysia. Journal of Applied Mechanical Engineering, 3(132), 1–7.
Elfstrom, G. (2007). History of test facility design expertise at Aiolos Engineering Corporation. In 45th AIAA Aerospace Sciences Meeting and Exhibit.
White, F. M., & Corfield, I. (2006). Viscous fluid flow (Vol. 3). McGraw-Hill.
Barlow, J. B., Rae, W. H., Jr., & Pope, A. (2015). Low-speed wind tunnel testing. INCAS Bulletin, 7(1), 133.
Laster, M. (1988). Boundary layer simulation and control in wind tunnels (AGARD Advisory Report No. 224).
Gersten, K. (2009). Hermann Schlichting and the boundary-layer theory. In Hermann Schlichting–100 Years (pp. 3–17). Springer.
Giguère, P., & Selig, M. S. (1999). Aerodynamic effects of leading-edge tape on aerofoils at low Reynolds numbers. Wind Energy, 2(3), 125–136.
Vicroy, D. D., et al. (2014). Low-speed dynamic wind tunnel test analysis of a generic 53° swept UCAV configuration. In 32nd AIAA Applied Aerodynamics Conference.
Buzica, A., et al. (2018). Leading-edge roughness affecting diamond-wing aerodynamic characteristics. Aerospace, 5(3), 98.
Breitsamter, C. (2006). Strömungsphysik und Modellgesetze. Lecture handout, Technische Universität München.
Schlichting, H., & Gersten, K. (2006). Grenzschicht-Theorie. Springer-Verlag.
Houghton, E., Carpenter, P., Collicott, S. H., & Valentine, D. T. (2013). Aerodynamics for engineering students.
Anderson, J. D., Jr. (n.d.). Introduction to flight.
Taylor, G. S., & Gursul, I. (2004). Buffeting flows over a low-sweep delta wing. AIAA Journal, 42(9), 1737–1745.
Loechert, P., et al. (2018). Control device studies for yaw control without vertical tail plane on a 53° swept flying wing configuration. In 2018 Applied Aerodynamics Conference.
Vandam, C. P. (1989). High angle-of-attack aerodynamic characteristics of crescent and elliptic wings.
McParlin, S., et al. (2006). Low speed wind tunnel tests on the 1303 UCAV concept. In 24th AIAA Applied Aerodynamics Conference.
Schütte, A., Hummel, D., & Hitzel, S. M. (2010). Numerical and experimental analyses of the vortical flow around the SACCON configuration. In 28th AIAA Applied Aerodynamics Conference.
Coppin, J., et al. (2016). Prediction of control effectiveness for a highly swept unmanned air vehicle configuration. Journal of Aircraft, 55(2), 534–548.
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