Static Aeroelasticity Solution for Divergence Dynamic Pressure of Wing

This paper introduces the solution for calculating the divergence dynamic pressure of wing under subsonic speed based on static aeroelasticity. Several groups of results (q ~ θ values) are calculated and the divergence dynamic pressure can be obtained through two methods, i.e. making q ~ θ value curves or deducing divergence dynamic pressure formula based on the characteristics of equilateral hyperbola. According to several groups of calculated data, the error caused by the two methods is minor and can be ignored basically.