Aerodynamics performance of optimal wing profile on MAV wing / Siti Khatijah Hamdan

The optimum design for Micro Air Vehicle (MAV) fixed wing is Zimmerman based on the optimal efficiency, however, the effect of camber to aerodynamics performance on the Zimmerman design are not fully discovered by previous researchers due to wide range of airfoil profile. Thus, the objectives of this research are to compare the aerodynamics performance of Zimmerman wing design with different percentage of camber. Three types of Zimmerman wing design known as Profile 1, Profile 2 and Profile 3 with 3%, 6% and 12% of camber, respectively which has different polynomial equation are used for ANSYS-CFX simulations. The three types of wing are initially developed by using ANSYS-Design Modeler before the aerodynamic simulation executed based on ANSYS-CFX simulation. The results shows that the stall angle of attack (AOA) for Profile 2 is 35° which is 3° and 5° higher than Profile 1 and Profile 3, respectively. The maximum lift coefficient (CL ) results shows that Profile 3 has better CL at 179.19% and 22.89% higher than Profile 1 and Profile 2, respectively. Based on the minimum drag coefficient (^Dmin ) analysis, all three profile produceCDmin at AOA * 0°. However, at this stage, Profile 1 produce the lowest CDmin at 99.6% and 99.9% lower than Profile 2 and Profile 3, respectively. The moment coefficient analysis shows that Profile 3 shows the steepest curve slope at ACL/ACM which is 22% and 35.32% higher than Profile 2 and Profile 1, respectively. Based on aerodynamic efficiency (CL/CD) study, Profile 2 shows the highest CL/CD value at 10.1175 which is higher about 23.38%