Volume 41 Issue 2
Feb.  2026
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TIAN Yaming, LI Maoqiang, SUN Penghui, et al. Study on water cooling system performance of aviation piston engines at high altitude[J]. Journal of Aerospace Power, 2026, 41(2):20240300 doi: 10.13224/j.cnki.jasp.20240300
Citation: TIAN Yaming, LI Maoqiang, SUN Penghui, et al. Study on water cooling system performance of aviation piston engines at high altitude[J]. Journal of Aerospace Power, 2026, 41(2):20240300 doi: 10.13224/j.cnki.jasp.20240300

Study on water cooling system performance of aviation piston engines at high altitude

doi: 10.13224/j.cnki.jasp.20240300
  • Received Date: 2024-05-12
    Available Online: 2025-11-27
  • In order to improve the high-altitude performance of aviation piston engines, detailed design and research work were carried out from four aspects: one-dimensional theoretical verification calculation of heat exchanger, performance experiment, simulation of heat exchanger with air duct and UAV flight experiment. The one-dimensional theoretical calculation was carried out using the ε-NTU method. The concept of cold side mixing coefficient (η) was proposed, which represented the degree of air side mixing caused by the opening of fins. And the selection and verification of heat exchanger were completed; an engine ground performance experiment bench was built and the impact of the upwind temperature of the heat exchanger on the engine cylinder head temperature was analyzed. Besides, a joint simulation model of heat exchanger with air duct was used to predict the high-altitude effluent temperature of the engine, and flight experiment validation was completed. The results indicated that the temperature of the windward surface of the heat exchanger affected the engine cylinder head temperature directly, and the increase of cylinder head temperature was basically consistent with the increase of windward temperature. Validated by flight tests, the coupled simulation model for the air duct and heat exchanger exhibits a prediction error of less than 3.1% in terms of the engine cylinder head temperature, which is sufficient to meet the accuracy requirements for engineering calculations. If the joint design results of the heat exchanger with air duct can meet the heat dissipation requirements of engine at the highest altitude take off state, the engine water cooling system design can meet the full climbing usage requirements of UAV.

     

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