Numerical Study of Effects of Fuselage and Facility Wall on PSP Rotor Performance in Hover

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In the present study, numerical simulations of the pressure-sensitive paint (PSP) rotor in hover were conducted using a Reynolds-averaged Navier-Stokes computational fluid dynamics (CFD) flow solver based on unstructured mixed meshes. In the simulations, an improved laminar-turbulent transition model gamma - Re-theta t - CF+ was adopted for the prediction of laminar-turbulent onset phenomena involving crossflow-induced transition and flow separation. To capture vortices with high resolution, an improved scheme ESWENO-P was utilized for computing inviscid fluxes on Cartesian meshes. The predicted results such as transition onset locations and rotor aerodynamic performances in terms of thrust coefficient, torque coefficient, and figure of merit were compared with the experimental data. The effects of the fuselage and facility wall on PSP rotor performance in hover were also investigated.
Publisher
SPRINGER
Issue Date
2022-02
Language
English
Article Type
Article
Citation

INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, v.23, no.1, pp.19 - 30

ISSN
2093-274X
DOI
10.1007/s42405-021-00420-9
URI
http://hdl.handle.net/10203/292115
Appears in Collection
AE-Journal Papers(저널논문)
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