By using the semi experiential engineering arithmetic based on the ideology of area ratio, the slope of lift coefficient curve, the zero lift drag coefficient and the induced drag factor of double delta wing aircraft were calculated.

In allusion to the flight control of flapping wing air vehicle(FAV), a method of design the flight controller for FAV based on linear estimation is presented.

Starting from aircraft empennage’s non linear characteristic, the non linear reason is discribed,and the identification method of structure dynamic characteristic is discussed.

Hypersonic pitching damp measurements for a winged vehicle by model free flight;