Structural parameters of airfoil shaped strut flame stabilizer were designed based on the algorithm of NACA airfoil parameters. The impacts of maximum thickness position and thickness of trailing edge of airfoil shaped stabilizers on the total pressure recovery coefficient and length of recirculation zone were analyzed by numerical simulation. The results show that total pressure recovery coefficient of strut flame stabilizer increases firstly

then decreases sharply with the maximum thickness position of airfoil shaped stabilizer moving towards to trailing edge under the conditions of flow Mach number from 0.15 to 0.30. However

the length of recirculation zone shows a contrary trend. The smaller trailing edge thickness of trailing edge of airfoil shaped stabilizer means the greater maximum total pressure recovery coefficient. The length of recirculation zone is proportional to 1.5 power of thickness of trailing edge.