This paper reports on the results of a research project that investigated the spin and recovery characteristics of a multirole fighter aircraft. In the first phase, numerical/computational methods were used to predict full scale aircraft spin and recovery characteristics. The aerodynamic data used in the numerical study was obtained from rotary balance steady coning and oscillatory coning motion dynamic wind tunnel tests conducted on 1/13^th scale aircraft dynamic model. All the possible steady spin modes were numerically computed, a complete set of dynamic modes of the spinning aircraft were evaluated and six degree of freedom simulations of predicted flat spins were performed to investigate their dynamic stability and recovery characteristics. In the second phase, free-flight spin trials were conducted using 1/5^th scale dynamic model of the understudy aircraft to validate the results of the analytical spin studies. Dynamic characteristics of the analytically predicted flat spins were objectively compared with flat spins found in free-flight spin trials as a validation process. Our results reveal that the numerically predicted full scale aircraft spin and recovery dynamic characteristics correlate well with those estimated from model test flights. The present study is an important step toward objective comparison of numerical spin studies based on dynamic wind tunnel tests data with free-flight spin trials, yielding important guidelines and results for future aircraft spin studies.

本文报告了一个研究项目的结果，该项目调查了多用途战斗机的旋转和恢复特性。在第一阶段，使用数值/计算方法来预测全尺寸飞机的旋转和恢复特性。^{数值研究中使用的空气动力学数据来自于 1/13日}进行的旋转平衡稳定圆锥和振荡圆锥运动动态风洞试验。比例飞机动力学模型。对所有可能的稳态自旋模式进行了数值计算，评估了旋转飞机的一整套动态模式，并对预测的平旋进行了六自由度模拟，以研究其动态稳定性和恢复特性。^{在第二阶段，使用 1/5 th}进行自由飞行旋转试验研究飞机的比例动力学模型，以验证分析自旋研究的结果。将分析预测的平旋的动态特性与作为验证过程的自由飞行自旋试验中发现的平旋进行了客观比较。我们的结果表明，数值预测的全尺寸飞机旋转和恢复动态特性与模型试飞估计的相关性很好。本研究是朝着基于动态风洞测试数据的数值旋转研究与自由飞行旋转试验进行客观比较的重要一步，为未来的飞机旋转研究提供重要的指导和结果。