The response cross-correlation of the simply supported elastic panel is derived through the normal mode approach assuming the analytic formula for the space-time cross-correlation of pressure fluctuations and non-interference between the vibration modes. The author has proposed new quantites "Dynamic Effect Function (DEF)" and "Orientation Sensitivity Factor (OSF)" as the measures to estimate dependency of vibration modes on pressure fluctuation convecting velocity, response magnification due to difference of flow direction respectively. Numerical examples state that DEF of the fundamental mode (DEF11)takes the maximum among the vibration modes, and it is almost ten times larger than other modes, moreover OSF11 is nearly equal to unity for various rectangular plates, which means response of fundamental mode is very insensitive to panel orientation.
The problem of high-angle-of attack aerodynamic derivatives is approached as follows: Qualitative equation of aerodynamic derivatives are derived, assuming that the vortex sheet theory is applicable approximately to the flow field with the separation around a vibrating thin aerofoil at high-angle-of-attack. The one of above equations, the equation of pitching moment derivative, is examined and compared with experimental data. And then, theoretically undeterminate parameters in the equation are estimated. Using the variables and constants determined above, lift derivatives are predicted and compared with experimental values.