MATEC Web Conf.
Volume 304, 20199th EASN International Conference on “Innovation in Aviation & Space”
|Number of page(s)||8|
|Section||Flight Physics: Noise & Aerodynamics|
|Published online||17 December 2019|
Nonlinear vortex lattice method for stall prediction
Airbus, Loads & Aeroelastics,
316 Route de Bayonne,
2 Airbus, Future Projects Office, Paseo John Lennon S/N, 28906 Getafe, Spain
* Corresponding author: firstname.lastname@example.org
The stall behavior of an empennage is a crucial and conditioning factor for its design. Thus, the preliminary design of empennages requires a fast low-order method which reliably computes the stall behavior and which must be sensitive to the design parameters (taper, sweep, dihedral, airfoil, etc.). Handbook or semi-empirical methods typically have a narrow scope and low fidelity, so a more general and unbiased method is desired. This paper presents a nonlinear vortex lattice method (VLM) for the stall prediction of generic fuselage-empennage configurations which is able to compute complete aerodynamic polars up to and beyond stall. The method is a generalized form of the van Dam algorithm, which couples the potential VLM solution with 2.5D viscous data. A novel method for computing 2.5D polars from 2D polars is presented, which extends the traditional infinite swept wing theory to finite wings, relying minimally on empirical data. The method has been compared to CFD and WTT results, showing a satisfactory degree of accuracy for the preliminary design of empennages.
© The Authors, published by EDP Sciences, 2019
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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