Simulation of Effect of Airfoil MH32 with Variation Taper Ratio and Angle of Attack Coefficient Lift and Drag Fixed wing Unmanned Aircraft

Authors

  • Satworo Adiwidodo Politeknik Negeri Malang, Indonesia
  • Andy Hermawan Wijaya Politekhnik Negeri Malang, Indonesia

DOI:

https://doi.org/10.51278/ajse.v1i1.396

Keywords:

Simulation Effect Airfoil, Coefficient Lift, Coefficient Drag

Abstract

Nowadays, the aerospace sector is growing very rapidly. One of the newest technologies is unmanned aerial vehicle. This UAV has functions to monitor disaster, mapping, espionage and shooting target. Therefore it needs a plane that can fly fast and agile. To achieve these characteristics, one of the most important things is the design of the wings. Some of the important parameters contained in the wings are the type of airfoil, aspect ratio, wing area, taper ratio, and angle of attack. The article aims to analyze the type of airfoil MH32 as well as the effect of the parameter taper ratio with variations of 0.2, 0.4, 0.6 in variations of angle of attack  0 °, 3 °, 6 °, 12 ° and 15 ° to the value of coefficient of lift  and coefficient of drag. The method used in this research is experimental with a computational approach using a computer, the advantage of this method is that it does not need a real plane shape. The type of simulation used is Computational Fluid Dynamic (CFD) found in Ansys Fluent. From the simulation,  value of coefficient of lift, coefficient of drag, and image of pressure contour and streamline velocity were obtained. All the data was processed and analyzed, then  the result is that the taper ratio 0.4 has the highest lift to drag ratio of 19,417. It means that it has the highest value of the coefficient of lift and has the lowest coefficient of drag. These simulated results are validated with experimental from UIUC (University of Illinois at Urbana-Champaign) 1996. The conclusion of this study is that the smaller the taper ratio, the greater the value of the lift coefficient. Then increase the angle of attack to make the value of the lift coefficient is also getting bigger.

Keywords: Simulation Effect Airfoil, Coefficient Lift, Coefficient Drag

References

[1] Embang, JD (2016). 2D Analysis of Airfoil NACA 4412 Using Computional Fluids Dynamic on Variation of Mach Number and Angle of Attack. Thesis. Not Published. Faculty of Science and Technology. Sanata Dharma University: Yogyakarta.
[2] Hidayat, MF (2014). Aerodynamics Analysis of the NACA 0012 Airfoil with Ansys Fluent. Journal of Technology Studies, 10(2).
[3] Hidayat, MF, & Nofendri, Y. (2018). Selection of the Best Angle of Attack Airfoil Naca 0013 When Take Off Using Ansys Fluent. Journal of Energy Conversion and Manufacturing UNJ, 5(2), 58-66.
[4] Husnayati, N., & Moelyadi, MA (2013). Aerodynamic Analysis and Parametric Study Of CN-235 Wing At Cruise Condition. Journal of Aerospace Technology, 11(2).
[5] Kurniawan, D. (2018). Aerodynamic Analysis of the V-Tail Wing of a Male UAV (Unmanned Aerial Vehicle Medium Altitude Long Endurance) Due to Airflow Rate Using Computational Fluid Dynamic (CFD) Software.
[6] Lubis, MM (2012). Aerodynamics Analysis of Naca 2412 Airfoil on Glider Type Airplane Wing Using Computional Fluid Dynamic Based Software to Obtain Maximum Lifting Force. e-Dynamic, 2(2).
[7] Lubis, MM (2012). Aerodynamics Analysis of Naca 2412 Airfoil on Glider Type Airplane Wing Using Computional Fluid Dynamic Based Software to Obtain Maximum Lifting Force. e-Dynamic, 2(2).
[8] Setiawan, B. (2016). Simulation of the Effect of Airfoil Naca 4412 and MH60 with variations of Tapper Ratio on Cl and Cd of Unmanned Aircraft for Surveillance Mission (Doctoral dissertation, Gadjah Mada University).
[9] Sirojuddin, MR, Wibowo, SB, & Nugroho, G. (2019). Design and Testing of Lokeswara Unmanned Aircraft Flights. SENIATI Proceedings, 334-338.
[10] Güzelbey, , Eraslan, Y , Do?ru, M . (2019). Effects Of Taper Ratio On Aircraft Wing Aerodynamic Parameters: A Comparative Study. European Mechanical Science , 3 (1) , 18-23 . DOI: 10.26701/Ems.487516

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Published

2022-06-30

How to Cite

Adiwidodo, S., & Wijaya, A. H. (2022). Simulation of Effect of Airfoil MH32 with Variation Taper Ratio and Angle of Attack Coefficient Lift and Drag Fixed wing Unmanned Aircraft. Asian Journal Science and Engineering, 1(1), 23–36. https://doi.org/10.51278/ajse.v1i1.396

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