Abstract: This paper gives an introduction to the wind tunnel experimental technique intended for the investigation of pitching dynamic derivative of a spinning projectile having high fineness ratio.It describes the test program, structure of the balance and the model, as well as the experimental results. The tests were made under the following conditions : range of Mach numbers :0.5 to 3; angle of attack: 0, 4 and 8 deg; maximum sping rate of the projectile: approximantely 15000r/min. The experimental results indicate that the test program is feasible, the experimental setup displays fine performance; and the results are rel iable. There appears to be no detectable spinning effect on the pitching dynamic derivative.