A new experimental technique has been developed to measure the pressure distribution over the surface of a rotating model in a wind tunnel for various spin rates, free-stream Mach numbers, and angles of attack. In this method, all of the measuring instruments are placed inside the rotating model which eliminated previous operational limitations and technical problems associated with attempts to measure the Magnus effect. The validity and reliability of the measured data was verified by comparing the integrated surface pressure values and aerodynamic forces, with those directly measured from an internal strain gauge balance. From the acquired surface pressure data distribution of both local and total Magnus force on the model as well as the interpretation of the boundary layer and flow separation effects on the rotating model could be determined. The Magnus force distribution shows that the local Magnus force increases along the length of the model and the maximum local Magnus force occurs at the end of the projectile. The acquired experimental data were further compared with the numerical simulations and satisfactory results were achieved. This new experimental technique can be easily applied to a variety of model configurations testing at different Mach numbers, spin rates, angles of attack, etc.

已经开发出一种新的实验技术来测量风洞中旋转模型表面上各种旋转速度，自由流马赫数和迎角的压力分布。在这种方法中，所有测量仪器都放置在旋转模型内部，从而消除了先前的操作限制以及与尝试测量马格努斯效应相关的技术问题。通过将积分表面压力值和空气动力与通过内部应变仪天平直接测量的积分表面压力值和空气动力进行比较，验证了测量数据的有效性和可靠性。根据所获得的局部和总马格努斯力在模型上的表面压力数据分布，以及边界层的解释和流动分离对旋转模型的影响，可以确定。马格努斯力分布表明，局部马格努斯力沿模型的长度增加，最大局部马格努斯力出现在弹丸的末端。将获得的实验数据与数值模拟进行了进一步比较，获得了满意的结果。这项新的实验技术可以轻松地应用于以不同马赫数，旋转速度，攻角等进行的各种模型配置测试。