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Efficient aerodynamic derivative calculation in three-dimensional transonic flow

Published online by Cambridge University Press:  10 July 2017

R. Thormann  and
S. Timme
R. Thormann*
Affiliation:
School of Engineering, University of Liverpool, United Kingdom
S. Timme
Affiliation:
School of Engineering, University of Liverpool, United Kingdom
*
reik.thormann@liverpool.ac.uk
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Abstract

One key task in computational aeroelasticity is to calculate frequency response functions of aerodynamic coefficients due to structural excitation or external disturbance. Computational fluid dynamics methods are applied for this task at edge-of-envelope flow conditions. Assuming a dynamically linear response around a non-linear steady state, two computationally efficient approaches in time and frequency domain are discussed. A non-periodic, time-domain function can be used, on the one hand, to excite a broad frequency range simultaneously giving the frequency response function in a single non-linear, time-marching simulation. The frequency-domain approach, on the other hand, solves a large but sparse linear system of equations, resulting from the linearisation about the non-linear steady state for each frequency of interest successively. Results are presented for a NACA 0010 aerofoil and a generic civil aircraft configuration in very challenging transonic flow conditions with strong shock-wave/boundary-layer interaction in the pre-buffet regime. Computational cost savings of up to 1 order of magnitude are observed in the time domain for the all-frequencies-at-once approach compared with single-frequency simulations, while an additional order of magnitude is obtained for the frequency-domain method. The paper demonstrates the readiness of computational aeroelasticity tools at edge-of-envelope flow conditions.

Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1244 , October 2017 , pp. 1464 - 1478
Copyright
Copyright © Royal Aeronautical Society 2017 

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