مطالعه عددی بهبود عملکرد آیرودینامیکی ابزار برآافزا در ایرفویل دو المانی

نوع مقاله : مقاله پژوهشی

نویسندگان

• میثم ایزدی ¹
• سید آرش سید شمس طالقانی ²
• رضا خاکی ³

¹ دانشجوی دکتری پژوهشگاه هوافضا

² عضو هیات علمی پژوهشگاه هوافضا

³ دانشیار، دانشگاه علوم و فنون هوایی شهید ستاری

10.22067/jacsm.2022.79293.1142

چکیده

هدف از این تحقیق بهبود عملکرد آیرودینامیکی ایرفویل ناکا-23012 مجهز به ابزار برآافزای لبه فرار با تغییر در پارامترهای هندسی آن است. در این تحقیق حل معادلات ناویر-استوکس در شرایط جریان آشفته و تراکم‌ناپذیر با بهره‌گیری از نرم‌افزار فلوئنت صورت پذیرفته است. بعد از فرایند مدلسازی ایرفویل و فلپ در زوایای فلپ متفاوت (5 الی 30 درجه)، شبکه‌بندی بی ‌سازمان در نرم‌افزار گمبیت تولید شد و بهبود عملکرد آیرودینامیکی ناشی از تغییرات ایجاد شده در پارامترهای هندسی مورد بررسی قرار گرفت. جریان از نوع دائم، متلاطم و تراکم‌ناپذیر فرض شده و الگوریتم حل معادلات نیز فشار مبنا انتخاب شده است. محدوده عدد رینولدز جریان 10⁶´6/3 بوده و مدل آشفتگی مورد استفاده کا-اپسیلون در نظر گرفته شده است. مقایسه نتایج و مشخصه­های آیرودینامیکی ایرفویل مجهز به فلپ پس از ایجاد تغییرات در پارامترهای هندسی در نرم‌افزار فلوئنت، نشان می‌دهد که ضرایب آیرودینامیکی به صورت قابل ملاحظه­ای (حدود 15%) بهبود یافته و همچنین جدایش جریان، به سمت انتهای فلپ جابه‌جا شده است. همچنین بررسی گرادیانهای فشار و سرعت در مقاطع مختلف، نشان می‌دهند که تغییرات بسیار مؤثر بوده و در مقایسه با مقاله مرجع توزیع بهتری صورت پذیرفته است.

کلیدواژه‌ها

• ابزار برآافزا
• فلپ‌های تک‌شکافه
• پارامترهای هندسی فلپ
• عملکرد آیرودینامیکی

موضوعات

• آئرودینامیک

---

عنوان مقاله [English]

Numerical Study of Improving the Aerodynamic Performance of the High Lift Devices in the Two-Element Airfoil

نویسندگان [English]

• Meysam Izadi ¹
• Arash shams taleghani ²
• Reza Khaki ³

¹ PhD candidate, Aerospace Research Institute

² Aerospace Research Institute

³ Assoc. Prof. Shahid Sattari Aeronautical University

چکیده [English]

The aim of this research is to improve the aerodynamic performance of a NACA-23012 airfoil equipped with a High lift device by changing its geometric parameters. In this research, Navier-Stokes equations are solved in turbulent and incompressible flow conditions using Fluent software. After the airfoil and flap modeling process, at different flap angles (5 to 30 degrees), unstructured meshing was produced in Gambit software and the improvement of aerodynamic performance due to changes in geometric parameters was investigated. The flow is assumed to be steady, turbulent and incompressible, and the algorithm for solving the equations is also selected as pressure-based. The flow Reynolds range is 3.6*10⁶ and the turbulence model used is realizable k-epsilon. Comparison of the results and aerodynamic characteristics of the airfoil equipped with a flap after making changes in the geometric parameters in the Fluent software, shows that the aerodynamic coefficients are improved significantly (about 15%) and also the flow separation is shifted towards the end of the flap. Also, the investigation of the pressure and velocity gradients at different stages show that the changes are very effective and better distributed compared to the reference article.

کلیدواژه‌ها [English]

• High Lift Devices
• Single Slotted Flaps
• Aerodynamic Optimization
• Unstructured Grid

مراجع

[1] M. Izadi, R. Khaki, A. Shams Taleghani, “A study of the effects of smart flap on model airfoil of fighter,” Journal of Aeronautical Engineering, vol. 22, no. 2, Pp. 80-97, April 2020. (in Persian)

[2] E. Najafi, S. Abdollahipour, A. Shams Taleghani, “Investigation of synthetic jet actuator position in delaying separation of a supercritical airfoil,” Journal of Aeronautical Engineering, vol. 24, Issue 2, Pp. 83-96, March 2022.

[3] A. Shams Taleghani, A. Shadaram, M. Mirzaei, “Effects of duty cycles of the plasma actuators on improvement of pressure distribution above a NLF0414 airfoil,” IEEE Transactions on Plasma Science, vol. 40, no. 5, Pp. 1434-1440, 2012.

[4] A. Salmasi, A. Shadaram, A. Shams Taleghani, “Effect of plasma actuator placement on the airfoil efficiency at post stall angles of attack,” IEEE Transactions on Plasma Science, vol. 41, no. 10, Pp. 3079-3085, 2013.

[5] A. Shams Taleghani, A. Shadaram, M. Mirzaei, “Effects of duty cycles of the plasma actuators on improvement of the pressure distribution over NLF0414 airfoil,” Modares Mechanical Engineering, vol. 12, no. 1, pp. 106-114, 2012. (in Persian)

[6] A. Salmasi, A. Shadaram, A. Mirzaei, A. Shams Taleghani, “Numerical and experimental investigation on the effect of a plasma actuator on NLF0414 airfoils efficiency after the stall,” Modares Mechanical Engineering, vol. 12, no. 6, Pp. 104-116, 2013. (in Persian)

[7] A. Shams Taleghani, A. Shadaram, M. Mirzaei, “Experimental Investigation of Active Flow Control for Changing Stall Angle of a NACA0012 Airfoil Using Plasma-Actuator,” Fluid Mechanics and Aerodynamics Journal, vol. 1, Pp. 89-97, 2012. (in Persian)

[8] M. Mohammadi, A. Taleghani, “Active Flow Control by Dielectric Barrier Discharge to Increase Stall Angle of a Naca0012 Airfoil,” Arab J Sci Eng, vol. 39, Pp. 2363–2370, 2014.

[9] M. Mirzaei, A. Taleghani, A. Shadaram, “Experimental study of vortex shedding control using plasma actuator,” Applied Mechanics and Materials, vol. 186, Pp. 75-86, 2012.

[10] A. Shams Taleghani, A. Shadaram, M. Mirzaei, S. Abdolahipour, “Parametric study of a plasma actuator at unsteady actuation by measurements of the induced flow velocity for flow control,” Journal of the Brazilian Society of Mechanical Sciences and Engineering, vol. 40, no. 4, Pp.1-13, 2018.

[11] A. Taleghani, A. Shadaram, M. Mirzaei, “Experimental investigation of geometric and electrical characteristics by measurements of the induced flow,” Modares Mechanical Engineering, vol. 12, no. 5, Pp. 132- 145, 2012. (in Persian)

[12] A. Shams Taleghani, “Numerical and Parametric investigation of Suction over a Cylinder for Reduction of Flow Unsteadiness and vortex,” Journal of Mechanical Engineering, vol. 49, no. 3, Pp. 183-192, 2019. (in Persian)

[13] S. Abdolahipour, M. Mani, A. Shams Taleghani, “Pressure Improvement on a Supercritical High-Lift Wing Using Simple and Modulated Pulse Jet Vortex Generator,” Flow Turbulence Combustion, vol. 109, Pp. 65–100, 2022.

[14] S. Abdolahipour, M. Mani, A. Shams Taleghani, “Enhancing the high-lift properties of a supercritical wing by means of a modulated pulse jet actuator,” Technical Physics Letters, . (Berlin: Springer) in press, 2022.

[15] S. Abdolahipour , M. Mani, A. Shams Taleghani, “Experimental Investigation of Flow Control on a High-Lift Wing Using Modulated Pulse Jet Vortex Generator,” Journal of Aerospace Engineering (ASCE), vol. 35, Issue 5, 2022.

[16] S. Abdolahipour, M. Mani, A. Shams Taleghani, “Parametric study of a frequency-modulated pulse jet by measurements of flow characteristics,” Physica Scripta, vol. 96, no. 12, 2021.

[17] S. Abdolahipoor, A. Mardani, A. Shams Taleghani, “Effects of pulsed counter flow jets on aerothermodynamics performance of a Re-Entry capsule at supersonic flow,” Aerospace Knowledge and Technology Journal, vol. 5,no. 1, Pp. 55-65, 2016. (in Persian)

[18] M. Taeibi Rahni, A. Shams Taleghani, M. Sheikholeslam, M. Ahmadi, “Computational simulation of water removal from a flat plate, using surface acoustic waves,” Wave Motion, vol. 111, no. 12, 2022.

[19] M. Sheikholeslam Noori, M. Taeibi Rahni, A. Shams Taleghani, “Numerical analysis of droplet motion over a flat plate due to surface acoustic waves,” Microgravity Science and Technology, vol. 32, no. 4, Pp. 647-660, 2020.

[20] M. Sheikholeslam Noori, A. Shams Taleghani, M. Taeibi Rahni, “Surface acoustic waves as control actuator for drop removal from solid surface,” Fluid Dynamics Research, vol. 53, no. 4, 2021.

[21] M. Sheikholeslam Noori, A. Shams Taleghani, M. Taeibi Rahni, “Phenomenological Investigation of Drop Manipulation Using Surface Acoustic Waves,” Microgravity Science and Technology, vol. 32, no. 6, Pp. 1147-1158, 2020.

[22] M. Sheikholeslam Noori, M. Taeibi Rahni, A. Taleghani, “Effects of contact angle hysteresis on drop manipulation using surface acoustic waves,” Theoretical and Computational Fluid Dynamics, vol. 34, no. 1, Pp. 145-162, 2020.

[23] A. Ghanbari Motlagh, S. Abdolahipour, A. Shams taleghani, “Flow control by magnetohydrodynamic field method at the supersonic air intake,” Aerospace Knowledge and Technology Journal, vol. 9, no. 1,Pp. 157-170, 2020. (in Persian)

[24] A. Shams taleghani, A. Ghanbari Motlagh, S. Abdolahipour, “Numerical Study of the Effects of Magneto hydrodynamic Field on Shock-Induced Flow Separation,” Fluid Mechanics and Aerodynamics Journal, vol. 9, no. 2, Pp. 17-28, 2021. (in Persian)

[25] M. Yadegari, A. Shams Taleghani, “Porous Media Applications in Shock Attenuation on Suction side of an Airfoil,” Aerospace Knowledge and Technology Journal, vol. 3, no. 1, Pp. 61-71, 2014. (in Persian )

[26] M. Yadegari, A. Shams Taleghani, “A Parametric Study for Passive Control of Shock-Boundary Layer Interaction of an Airfoil with Porous Media in a Transonic Flow,” Fluid Mechanics and Aerodynamics Journal, Vol. 3, Number 4, Pp. 73-86, 2015. (in Persian)

[27] M. Yadegari, A. Shams Taleghani, “Numerical Study of Shock-Boundary Layer Interaction on an Airfoil with Cavity and Porous Surface: Parametric Investigation in a Transonic Flow,” Journal of Solid and Fluid Mechanics, Vol. 6, No. 2, Pp. 271-284, 2016. (in Persian)

[28] R. Hammerton, W. Su, G. Zhu, S. Shan Min Swei, “Optimum distributed wing shaping and control loads for highly flexible aircraft,” Journal of Aerospace Science and Technology, Elsevier Masson SAS, vol. 79, Pp. 255-265, 2018.

[29] H. Wenxing, L. Chun, “Performance improvement of adaptive flap on flow separation control and its effect on VAWT,” Journal of Energy, Elsevier Ltd, vol. 213, Pp. 356- 378, 2020.

[30] G. Luiz Olichevis Halila, A. Pequeno Antunes, R. Galdino da Silva, J. Luiz Azevedo, “Effects of boundary layer transition on the aerodynamic analysis of high-lift systems,” Journal of Aerospace Science and Technology, Elsevier Masson SAS, vol. 90, Pp. 233-245, 2019.

[31] S. Abdolahipour, M. Mani, A. Shams Taleghani, “Experimental Investigation of Aerodynamic Characteristics of a Supercritical Two-Element High-Lift Airfoil,” Aerospace Knowledge and Technology Journal, 10, 1, 2021. (in Persian)

[32] K. Biber, “Stall hysteresis of an airfoil with slotted flap,” Journal of Aircraft, American Institute of Aeronautics and Astronautics Inc., vol. 42, Pp. 1462-1470, 2005.

[33] A. Noriega, M. Balas, P. Anderson, “Robust Adaptive Control of a Weakly Minimum Phase General Aviation Aircraft, Conference of Procedia Computer Science,” Elsevier B.V., vol. 95, Pp. 497-506, 2016.

[34] M. Nemati, A. Jahangirian, “Robust aerodynamic morphing shape optimization for high-lift missions,” Journal of Aerospace Science and Technology, Elsevier Masson SAS, vol. 103, Pp. 167-183, 2020.

[35] S. Chen, F. Zhang, M. Khalid, “Aerodynamic Optimization for a High-Lift Airfoil/Wing Configuration,” 22^nd Applied Aerodynamics Conference and Exhibit, August 2004.

[36] L. Soulat, A. Fosso Pouangué, S. Moreau, “A high-order sensitivity method for multi-element high lift device optimization,” Journal of Computers & Fluids , Elsevier Ltd, vol. 124, Pp. 105-116, January 2016.

[37] L. Weishuang, T. Yun, L. Peiqing, “Aerodynamic optimization and mechanism design of flexible variable camber trailing-edge flap,” Chinese Journal of Aeronautics, vol. 30, Pp. 988-1003, 2017.

[38] L. Qingsong, M. Weipao, L. Chun, H. Winxing, Z. Haitian, D. Yunhe, “Effects of trailing-edge movable flap on aerodynamic performance and noise characteristics of VAWT,” Journal of Energy, Elsevier Ltd, vol. 189, 2019.

[39] M. Zhang, Z. Chen, Z. Tan, G. Wenting, D. Li, C. Yuan, B. Zhang, “Effects of stability margin and thrust specific fuel consumption constrains on multi-disciplinary optimization for blended-wing-body design,” Chinese Journal of Aeronautics, vol. 32, Pp. 1847-1859, 2019.

[40] J. N. Kudva, C. A. Martin, L. B. Scherer, A. P. Jardine, A. R. McGowan, R. C. Lake, G. Sendecky, B. Sanders, “Overview of the DARPA/AFRL/NASA Smart Wing Program,” Proceedings Of SPIE, vol. 3674, Pp. 230-236, 2003.

[41] J. Wild, “Mach and Reynolds Number Dependencies of the Stall Behavior of High-Lift Wing-Sections,” Journal of Aircraft, vol. 50, no. 4, Elsevier Ltd, vol. 189, 2013.

[42] F. Chen, J. Yu, Y. Mei, “Aerodynamic design optimization for low Reynolds tandem airfoil,” Aerospace Engineering Journal, vol. 232, June 2017.

[43] K. Mohseni, Mittal, R., “Synthetic Jets: Fundamentals and Applications,” CRC Press, 2014.

[44] J. G. Lowry, “wind-tunnel investigation of naca 23012 airfoil with several arrangements of slotted flaps with extended lips,” Technical notes of National Advisory Committee for Aerospace, no. 808, may1941.

[45] I. Angelov, C. Velcova, “Influence of а slotted flap gap size on the aerodynamic characteristics of a light aircraft wing at taking off and landing,” 7^th International Conference on Energy Efficiency and Agricultural Engineering, December, (2020).