Experimental study of the effect of the LEX angle on the flow pattern of a diamond wing with an airfoil cross section

Journal of Visualization - Tập 26 - Trang 1247-1262 - 2023
Mohammad Reza Hashemi1, Mojtaba Dehghan Manshadi2
1Department of Mechanical Engineering, University of Birjand, Birjand, Iran
2Faculty of Mechanical Engineering, Malek-Ashtar University of Technology, Tehran, Iran

Tóm tắt

In this research, the effect of the leading-edge extension (LEX) angle on the flow pattern upstream and downstream of the diamond wing has been investigated experimentally. The measurement of turbulence intensity by the hot-wire and the measurement of pressure on the wing by the five-hole probe in a closed-circuit wind tunnel at a free flow velocity of 12.5 m/s, which is equivalent to the Reynolds number of 202,000, have been carried out. In order to better observe the flow physics and qualitative analysis of the vortex flow, the smoke tunnel has been used. In this case, the free flow velocity is equal to 1 m/s equivalent to the Reynolds number of 16,000. The results indicated that the increase in the LEX sweep angle has led to an increase in the strength of the vortex, and with the increase in the angle of attack, the vortices have moved further away from the wing's upper surface. Also, the increase in the angle of attack shifts the breakdown location upstream, eventually reaching a complete wing stall. The use of LEX produced a vortex flow, which delayed the vortex breakdown by increasing the kinetic energy in the vortex core. The turbulence downstream of the wing is reduced with the breakdown delay. The frequency analysis showed that at the vortex core, the instantaneous velocity fluctuations are very high, which indicates an increase in turbulent kinetic energy.

Tài liệu tham khảo

Brandt S, Crisler W, Forystek R and Smith J (2011) Comparative evaluation of butterfly and 4-post tails on a 5th-generation fighter configuration. In: 11th AIAA Aviation Technology Integration and Operations Conference 2011 Buzica A, Debschüt L, Breitsamter C (2018) Leading-edge roughness affecting diamond-wing aerodynamic characteristics. Aerosp Sci Technol 5(3):1–23 Çelik A, Yavuz M (2016) Effect of edge modifications on flow structure of low swept delta wing. AIAA J 54(5):1789–1797 Chou M, Miau J (2021) Vortex interaction on a LEX configuration. J vis 24:1189–1205 Daniels RK, Babu N, Jacob B, Issac J, Mathew EM (2019) Computational study of the pressure field of a five hole probe head and Kiel probe head. Glob Res Dev J Eng, 2 4 Dehghan AA, Kazemi Esfeh M, Manshadi MD (2013) Natural ventilation characteristics of one-sided wind catchers: experimental and analytical evaluation. Energy Build 61:366–377 Gordnier E, Visbal M (2005) Compact difference scheme applied to simulation of low-sweep deltawing flow. AIAA J 43(8):1744–1752 Gueraiche D, Popov S (2018) Improving the aerodynamics of a transport aircraft wing using a delta planform wingtip leading edge extension. Civil Aviat High Technol 21(1):124–136 Hitzel S, Boelens O, Rooij M, Hövelmann A (2016) Vortex development on the AVT-183 diamond wing configuration–numerical and experimental findings. Aerosp Sci Technol 57:90–102 Inamdar A, Thakur N, Pal D and Mohite A (2021) Flexible wing structure and variable-sweep wing mechanism. Int Res J Eng Technol, 8 3 Karasu I, Durhasan T (2020) Flow characteristics over double delta wings at low Reynolds numbers. J Aerosp Eng 33(4):04020038 Kazemi Esfeh M, Sohankar A, Shirani E (2021) Influence of rounding corners on the wake of a finite-length cylinder: An experimental study. Int J Heat Fluid Flow 91:108854 Kwiek A, Figat M (2016) LEX and wing tip plates’interaction on the rocket plane in tailless configuration. Aeronaut J 120(1224):255–270 Lowson M (1990) Visualization measurements of vortex flows. J Aircr 28(5):320–327 Luckring J (2019) The discovery and prediction of vortex flow aerodynamics. Aeronaut J 123(1264):729–804 Lum C, Sandhu N, Diebold JM, Woodard B, and Bragg MB (2017) The application of a five-hole probe wake-survey technique to the study of swept wing icing aerodynamics. In: 9th AIAA Atmospheric and Space Environments Conference, pp 4374 Mahgoub A, Cortelezzi L (2020) Vortex flow and aerodynamic performance of a reverse delta wing. AIAA J 58(2):537–549 Manshadi MD, Kazemi Esfeh M (2016) Experimental investigation of flowfield over an iced aerofoil. Aeronaut J 120(1227):735–756 Manshadi MD, Eilbeigi M, Sobhani MK, Bazaz Zadeh M, Vaziry M (2016) Experimental study of flow field distribution over a generic cranked double delta wing. Chin J Aeronaut 29(5):1196–1204 Miloud KB, Dghim M, Fellouah H, Ferchichi M (2020) Free-stream turbulence interaction with a wing-tip vortex. J Wind Eng Ind Aerodyn 206:104211 Nikolic V (2006) Planform Effects on Wing-Movable Tip Strake Aerodynamic Performance. In: 6th AIAA Aviation Technology Integration and Operations Conference. Pereira FP, Eça L, Vaz G (2019) Simulation of wingtip vortex flows with Reynolds-averaged Navier–Stokes and scale-resolving simulation methods. AIAA J 57(3):932–948 Pfnür S, Oppelt S, Breitsamter Ch (2019) Yaw-control efficiency analysis for a diamond wing configuration with outboard split flaps. CEAS Aeronaut J 10:645–663 Saeidinezhad A, Dehghan A, Manshadi MD (2015) Nose shape effect on the visualized flow field around an axisymmetric body of revolution at incidence. J vis 18:83–93 Shah G (1991) Wind Tunnel Investigation of Aerodynamic and Tail Buffet Characteristics of Leading-Edge Extension Modifications to the F/A-18. In: 18th Atmospheric flight mechanics conference, pp 395–412 Shen L, Wen Ch (2018) Oscillations of leading-edge vortex breakdown locations over a delta wing. AIAA J 56(6):2113–2118 Shen L, Chen Z, Wen Ch (2018) Experimental investigation of the flow structure over a delta wing via flow visualization methods. J vis Exp 134:e57244 Sinha A, Suthar A, Sahoo S, Pawar AA, Ranjan K and Saha S (2017) Effect of sweep angle on wing-strake vortex interaction and breakdown over double delta wings. In: 2017 First international conference on recent advances in aerospace engineering, pp 1–6 Sohn M (2010) Effect of apex strake incidence-angle on the vortex development and interaction of a double-delta wing. Exp Fluids 48:565–575 Touzopoulos P, Boviatsis D, Zikidis K (2017) Constructing a 3D model of a complex object from 2D images for the purpose of estimating its radar cross section (RCS). J Comput Model 7:15–28 Viviani A, Aprovitola A, Iuspa L, Pezzella G (2020) Low speed longitudinal aerodynamics of a blended wing-body re-entry vehicle. Aerosp Sci Technol 107:106303 Wang Ch, Gao Q, Wei R, Li T, Wang J (2016) 3D flow visualization and tomographic particle image velocimetry for vortex breakdown over a non-slender delta wing. Exp Fluids 57:1–13 Yaniktepe B, Rockwell D (2004) Flow Structure on a delta wing of low sweep angle. AIAA J 42(3):513–523 Yaniktepe B, Rockwell D (2005) Flow structure on diamond and lambda planforms trailing-edge region. AIAA J 43(7):1490–1500 Yi Y, Hu T, Liu P, Qu Q, Eitelberg G, Akkermans AD (2020) Dynamic lift characteristics of nonslender delta wing in large-amplitude-pitching. Aerosp Sci Technol 105:105937 Zhou Z, Huang J (2023) W-type flying wing radar cross-section analysis. Proc Inst Mech Eng Part G J Aerosp Eng 237(5):1094–1105 Zhu M, Qin N (2021) Balancing laminar extension and wave drag for transonic swept wings. AIAA J 59(5):1660–1672 Zikidis K, Skondras A, Tokas Ch (2014) low observable principles, stealth aircraft and anti-stealth technologies. J Comput Model 4(1):129–165 Zimmerman S, Philip J, Marino N, Klewicki J (2018) Downstream recovery of turbulence kinetic energy in the wake of a turbulent boundary layer wing-body junction flow. In: 21st Australasian Fluid Mechanics Conference.