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Non-inertial multiblock Navier-Stokes calculation for hovering rotor flowfields using relative velocity approach

Published online by Cambridge University Press:  04 July 2016

B. Zhong  and
N. Qin
B. Zhong
Affiliation:
Centre for Computational Aerodynamics Cranfield University, College of Aeronautics Bedford, UK
N. Qin
Affiliation:
Centre for Computational Aerodynamics Cranfield University, College of Aeronautics Bedford, UK
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Abstract

A three dimensional Navier-Stokes solver is presented for calculating the hovering rotor flowfield using Osher's approximate Riemann solver. The Navier-Stokes equations are recast in the attached blade relative system using relative flow velocities as variables. Multiblock techniques are used to obtain a structured grid around the blade. A modified MUSCL scheme is proposed to alleviate the inaccuracy in the discretisation of the relative variable formulation. The calculations are performed for a two-bladed model rotor on C-H, O-O and C-H cylindrical grid topologies respectively. Computational solutions show reasonably good agreement with the experimental data for different lifting cases. The difficulty and suitability of different grid topologies for capturing the tip vortex is illustrated. The differences between Euler and Navier-Stokes solutions and between wake modelling and wake capturing approaches are also revealed. The results indicate that the relative velocity approach can give reasonable results for hovering rotor flowfields if due care is taken in minimising possible numerical errors.

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1049 , July 2001 , pp. 379 - 389
Copyright
Copyright © Royal Aeronautical Society 2001 

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