COMPUTATIONAL FLUID DYNAMICS BASED WINGLET DESIGN AND ANALYSIS OF GL-1 GLIDER

• المؤلف الرئيسي: Muhammad, Diksan
• التنسيق: Final Project
• اللغة: Indonesia
• الوصول للمادة أونلاين: https://digilib.itb.ac.id/gdl/view/41567
• المؤسسة: Institut Teknologi Bandung

Winglet is the most effective device installed in wing tip to reduce induced drag which is the second largest contribution of drag especially in a low-speed aircraft. The drag is from wingtip vortex. In the previous study, GL-1 have not added yet by winglet and the aerodynamic efficiency was 27 or equal to 11.7 km maximum range. However, that value was below the conceptual design value which is 30 or equal to 13.7 km maximum range. The objective of the study is to increase aerodynamic efficiency of GL-1 to 30 by introducing the winglet. The problem a is determining winglet geometry that fulfill design target. So, the study of parametric method is carried out including winglet height, sweep angle, and taper ratio. To produce desired aerodynamic characteristics from the winglet, computational fluid dynamics method solving Reynold Averaged Shear Stress coupled with Shear Stress Transport and Gamma-Theta transition model is used. After winglet is installed to GL-1, the lift coefficient, CL, increases by 3.4106 percent, the drag coefficient, CD, decreases by 3.2086 percent, and aerodynamic efficiency (CL/CD).is increased by 6.8366 percent as well as the maximum range increases from 11.7 to 12.5 km.