This report presents a novel method of estimating neutral point of an aircraft using Dynamic wind tunnel simulation. The method uses pitch motion and lift force responses13; of dynamically scaled aircraft model flown in the wind tunnel for estimating Pitching moment and lift derivatives from which neutral point is deduced. The advantage of this method is the simplicity of model instrumentation and testing. The method is demonstrated using a generic delta winged aircraft model flown with pitch DOF in dynamic wind tunnel. Comparison of estimated neutral point location with that obtained from static tests on similar configuration show good agreement
