Abstract
The unmanned aerial vehicle (UAV) is becoming popular from last two decades and it has been utilizing in enormous applications such as aerial monitoring, military purposes, rescue missions, etc. Hence, the present work focused on the design of the UAV wing considering the CH10 airfoil. In this paper, the computational fluid dynamic analysis on CH10 cambered airfoil has been conducted to achieve the preliminary results on the aerodynamic lift and drag coefficients. The airfoil has a chord length of 1 meter and has been subjected to low Reynolds numbers of 500 000, which is the standard operating Reynolds number for UAV wing design. The C-type fluid domain has been constructed at 30C upstream and downstream of the airfoil to initialize the boundary conditions. The angle of attack ranging from 0 degrees to 14 degrees with the increment of 2 degrees has been done by changing the direction of the freestream velocity. The aerodynamic characteristics have been numerically computed using Spallart-Allmaras and Transient SST models. The aerodynamic coefficients achieved by these two models have been validated based on the XFOIL data. The contours of static pressure and velocity magnitude at 0 degrees, 5 degrees, 10 degrees, and 12 degrees angle of attack have been portrayed. The static pressure distribution around the airfoil has been visually observed to analyze its influence on the aerodynamic coefficients. The velocity magnitude relation to the static pressure distribution has been approved based on Bernoulli's equation such that increasing velocity magnitude has decreased the static pressure. The present results show that the Transient SST model has shown better flow prediction for an airfoil subjected to low Reynolds number flow.