Flow past triangular airfoil of variable thickness with low Reynolds number in Mars atmosphere

Aerodynamic research on Mars for the past few decades has increased in the development of optimum aerial vehicles for Mars. The current research aims to study the aerodynamics of a triangular airfoil in Mars atmospheric conditions and understand the future regions of flow improvement. A numerical investigation using a Finite Volume Solver has been performed for 0 degrees to 16 degrees angles of attack at low and high flow velocities. Low flow velocities ranging from Re = 3,000 to 7,000 have been considered for the investigation. The nonlinearity in Cl appears as the separation bubble begins to approach the apex on the suction surface. Apart from the separation bubble, a flow recirculation zone is generated for low and high Re. at alpha = 16 degrees. The highest aerodynamic performance is at alpha = 6 degrees.