翼型支板火焰稳定器结构参数的研究

以NACA翼型参数算法为基础进行翼型支板火焰稳定器设计,并采用数值模拟方法探讨了翼型稳定器最大厚度位置和截尾厚度两个结构参数对总压恢复系数和回流区长度的影响.结果表明:在来流马赫数为0.15~0.30的条件下,随着翼型稳定器最大厚度位置向尾缘方向后移,总压恢复系数先增大后急剧减少,回流区长度则呈现相反趋势;翼型稳定器截尾厚度越小,其最大总压恢复系数越大,且回流区长度与截尾厚度的1.5次方成正比.

Investigation on structural parameters of airfoil shaped strut flame stabilizer

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.