Experimental study on dynamic characteristics of delta wing in pitching motion

The Crst purpose of the research is to make a simple, comiact and inexpensive force balance, which will be improved and be applied to measure aerodynamic force in undesirable or severe condition like in very high temperature flow. The second is to investigate dynamic characteristics of aerodynamic forces and moment for a delta wing in pitching motion experimentally with the developed force balance, which is compared with static results. The third puqiose is to study aerodynamic characteristics of the pitching delta wing near the gmund and compared with those out of ground effect. A force balance in the shape of a ring to measure lift, drag .and pitching moment was developed, and was found to get these forces and moment witbin the error of about 7.5%. Existence of the ground fasten a stall and increases a maximum lift coefficient by 24% compared with tho& out of ground effect. Derivative of the measured pitching moment coefficient with respect to attack angle indi+tes that longitudinal static stability increases owing to the ground effect on the delta wing in pitching motion around at a stall angle of attack.