Volume 39 Issue 6
Jun.  2024
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YANG Liu, LIU Yu. Numerical simulation analysis of inlet flow field of anti-clockwise main rotor helicopter with twin engine[J]. Journal of Aerospace Power, 2024, 39(6):20210697 doi: 10.13224/j.cnki.jasp.20210697
Citation: YANG Liu, LIU Yu. Numerical simulation analysis of inlet flow field of anti-clockwise main rotor helicopter with twin engine[J]. Journal of Aerospace Power, 2024, 39(6):20210697 doi: 10.13224/j.cnki.jasp.20210697

Numerical simulation analysis of inlet flow field of anti-clockwise main rotor helicopter with twin engine

doi: 10.13224/j.cnki.jasp.20210697
  • Received Date: 2021-12-08
    Available Online: 2024-01-20
  • The flow field of an anti-clockwise main rotor helicopter with two engines in steady forward flight, side flight and hovering was simulated by numerical simulation method, and the total inlet pressure loss and inlet temperature rise under different flight states were obtained. The results showed that the average total pressure loss of the engine intake surface increased with the increase of steady forward flight speed, and the maximum was about 1.61%. During side flight, there was a large total pressure loss in the outer area of the downstream engine inlet and a large air temperature rise in the downstream engine inlet. At the same speed, the inlet temperature rise of the downstream engine was higher when flying on the right wind, which had greater influence on the engine performance. The maximum average total pressure loss of the engine inlet surface was about 1.14% under the hovering state. Compared with the flight data of this helicopter, the effectiveness of the numerical simulation results was verified. The result can provide a reference for domestic flight test subject planning and engine installation loss evaluation of the same type of helicopter.

     

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