Get 20M+ Full-Text Papers For Less Than $1.50/day. Subscribe now for You or Your Team.

Learn More →

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

Numerical Study of Effects of Fuselage and Facility Wall on PSP Rotor Performance in Hover 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 γ-Reϑt-CF+\documentclass[12pt]{minimal}\usepackage{amsmath}\usepackage{wasysym}\usepackage{amsfonts}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{mathrsfs}\usepackage{upgreek}\setlength{\oddsidemargin}{-69pt}\begin{document}$$\gamma - {\text{Re}}_{{\vartheta t}} - {\text{CF}}^{ + }$$\end{document} 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. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png International Journal of Aeronautical and Space Sciences Springer Journals

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

Loading next page...
 
/lp/springer-journals/numerical-study-of-effects-of-fuselage-and-facility-wall-on-psp-rotor-eTZyX0tijy

References (23)

Publisher
Springer Journals
Copyright
Copyright © The Korean Society for Aeronautical & Space Sciences 2021
ISSN
2093-274X
eISSN
2093-2480
DOI
10.1007/s42405-021-00420-9
Publisher site
See Article on Publisher Site

Abstract

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 γ-Reϑt-CF+\documentclass[12pt]{minimal}\usepackage{amsmath}\usepackage{wasysym}\usepackage{amsfonts}\usepackage{amssymb}\usepackage{amsbsy}\usepackage{mathrsfs}\usepackage{upgreek}\setlength{\oddsidemargin}{-69pt}\begin{document}$$\gamma - {\text{Re}}_{{\vartheta t}} - {\text{CF}}^{ + }$$\end{document} 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.

Journal

International Journal of Aeronautical and Space SciencesSpringer Journals

Published: Feb 1, 2022

Keywords: PSP rotor; γ-Reϑt-CF+\documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$\gamma - {\text{Re}}_{{\vartheta t}} - {\text{CF}}^{ + }$$\end{document} transition model; Facility wall effect; Fuselage effect; Mixed mesh flow solver

There are no references for this article.