针对某型航空活塞发动机提出一种基于中冷系统传热数学仿真的有效功率计算方法，并应用VB语言对该中冷系统传热仿真模型进行开发。通过试验数据对仿真模型的有效性进行验证。结果表明：中冷器冷侧出口温度、热侧出口温度的仿真计算值与试验值误差均在1.5%以内。利用该仿真模型，研究了风扇风量对航空活塞发动机有效功率的影响，并对空中有效功率恢复进行研究。结果表明：随着风扇风量的增加，风扇功率增幅变大，而发动机功率增幅降低。在二者的综合作用下，发动机有效功率随着风扇风量的增加先升高后下降。对于所研究的航空活塞发动机，当风扇风量为1 400 m³/h时，发动机有效功率达到最大，其最大值为101.6 kW。当飞行高度在2 000 m以下时，随着飞行高度的升高，发动机有效功率恢复系数小幅增加，当飞行高度在2 000 m以上时，发动机有效功率随着飞行高度的增加大幅降低。在海平面环境为50 ℃条件下，在7 000 m高度即便维持稳压箱压力不变，发动机有效功率恢复系数仅能达到92.2%。

A calculation method of effective power based on heat transfer mathematical simulation of intercooling system was proposed for an aviation piston engine, and the heat transfer simulation model of the intercooling system was developed with VB language. The validity of the simulation model was verified by the test data. The results show that the errors between the simulation values and the test values of the intercooler cold side outlet temperature and the hot side outlet temperature are within 1.5%. Using the simulation model, the influence of fan air flow on the effective power of the aviation piston engine was studied, and the air effective power recovery was studied. The results show that with the increase of fan air volume, the amplification of fan power increases, while the amplification of engine power decreases. Under the combined effect of the two, the effective power of the engine first increases and then decreases with the increase of fan air volume. For the aviation piston engine studied, when the fan air volume is 1 400 m³/h, the effective power of the engine reaches the maximum, which is 101.6 kW. When the flight altitude is below 2 000 m, the engine effective power recovery coefficient increases slightly with the increase of flight altitude, and when the flight altitude is above 2 000 m, the engine effective power decreases significantly with the increase of flight altitude. Under the condition of 50 ℃ at sea level, the effective power recovery coefficient of the engine at 7 000 m is only 92.2%.