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Flowfield of a helicopter submerged inlet with power output shaft

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Abstract

The submerged inlet is an attractive configuration for advanced helicopters due to its high stealth performance and low external drag. In this paper, a submerged inlet, integrated with a ROBIN helicopter fuselage and a simplified power output shaft, is experimentally and numerically investigated to obtain the basic flow characteristics under a freestream velocity of 23.6 m/s. The results indicate that the pylon ahead of the inlet induces a horseshoe vortex. Though the vortex is ingested into the inlet, it has little effect on the internal flows and can be neglected. When the airflow enters into the inlet, it interacts with the shaft with a large incidence angle, yielding a vortex pair. At the leeside of the shaft, the two side flows of the shaft impinge at the center plane, generating a local high-pressure region at the azimuthal angle of 180°, which forces the boundary layer to roll up a counter-rotating vortex pair. In addition, the airflow adjacent to the cowl lip accelerates rapidly, resulting in a local low-pressure region at the azimuthal angle of 0°. Therefore, the inlet duct has a strong circumferential pressure gradient, which originates from an azimuthal angle of 180° to 0° and induces a vortex pair at the azimuthal angle of 0°. The three vortex pairs are the main origins of the distortion at the duct exit plane, among which the one near the cowl lip with the azimuthal angle of 0° plays the dominant role. Additionally, as the velocity ratio increases from 3.9 to 5.5, the circumferential pressure gradient and the cowl lip vortex get intensified, which causes that the total-pressure recovery coefficient drops by 0.5% and the distortion index increases by 28%.

Graphic abstract

A submerged inlet, integrated with a ROBIN helicopter fuselage and a simplified power output shaft, is experimentally and numerically investigated. Three vortex pairs, which locate at the azimuthal angle of 0°, the leeside of the shaft, and 180° of the inlet surface, are the main origins of the distortion of the inlet, among which the one near the cowl lip with the azimuthal angle of 0° plays the dominant role. As the velocity ratio increases, the circumferential pressure gradient gets intensified, leading to stronger vortex pairs.

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Abbreviations

x,y,z :

Cartesian coordinates, m

L :

Axial length of the helicopter, m

D :

Outer diameter of the inlet exit, m

V 0 :

The freestream velocity, m/s

V e :

Exit velocity of the submerged inlet, m/s

p :

Static pressure, kPa

p 0 :

Freestream static pressure, kPa

C v :

Velocity ratio, \(C_{\text{v}} = \frac{{V_{\text{e}} }}{{V_{0} }}\)

\(\rho_{0}\) :

Freestream density, kg/m3

C p :

Static pressure coefficient, \(C_{p} = \frac{{p{\text{ - p}}_{{0}} }}{{0.5\rho_{{0}} {\text{V}}_{{0}}^{{2}} }}\)

\(\theta\) :

Azimuthal angle

\(p_{av}^{*}\) :

Average total pressure at aerodynamic interface plane (AIP), kPa

\(\overline{p}_{\min \,60^\circ }^{*}\) :

The minimum total pressure in a sector region with the sector angle of 60°, kPa

\(q_{av}\) :

Average dynamic pressure at AIP, kPa

DC 60 :

Circumferential distortion index, \(DC_{60} = \frac{{p_{av}^{*} - \overline{p}_{\min \,60^\circ }^{*} }}{{q_{av} }}\)

σ :

Total pressure recovery coefficient at the exit of the inlet

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Acknowledgements

This work was funded by the National Natural Science Foundation of China (Grants 51906104, 11532007, 12025202 and 11772156), the Natural Science Foundation of Jiangsu Province (Grant BK20190385), Aeronautics Power Foundation (Grants 6141B09050387, 6141B09050341), Jiangsu Provincial 333 High-level Talent Cultivation Project (Grant BRA2018031), the Priority Academic Program Development of Jiangsu Higher Education Institutions, and the Fundamental Research Funds for the Central Universities (Grants 1002-YAH18026 and 1002-56XAA19050).

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Authors and Affiliations

  1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, 210016, China

    He-Xia Huang, Hui-Jun Tan, Zheng-Kang Lin, Zi-Jie Li, Shu Sun & Hao Chen

  2. School of Aerospace Engineering, Tsinghua University, Beijing, 100084, China

    He-Xia Huang & Zhi-Xiang Xiao

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  1. He-Xia Huang
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Correspondence to Hui-Jun Tan.

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Executive Editor: Yue Yang

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Huang, HX., Tan, HJ., Lin, ZK. et al. Flowfield of a helicopter submerged inlet with power output shaft. Acta Mech. Sin. 37, 156–168 (2021). https://doi.org/10.1007/s10409-020-01029-z

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