Combined high-speed and high-lift wing aerodynamic optimization using a coupled VLM-2.5D RANS approach
| Autor: | Eric Laurendeau, Gerald Carrier, Matthieu Parenteau |
|---|---|
| Přispěvatelé: | École Polytechnique de Montréal (EPM), DAAA, ONERA, Université Paris Saclay (COmUE) [Meudon], ONERA-Université Paris-Saclay |
| Jazyk: | angličtina |
| Rok vydání: | 2018 |
| Předmět: |
[PHYS]Physics [physics]
020301 aerospace & aeronautics Computer science RANS Aerospace Engineering Stall (fluid mechanics) 02 engineering and technology Aerodynamics Solver AERODYNAMIC OPTIMIZATION 01 natural sciences 010305 fluids & plasmas Aerodynamic force [SPI]Engineering Sciences [physics] 0203 mechanical engineering Control theory 0103 physical sciences CMA-ES Vortex lattice method NON-LINEAR VORTEX LATTICE METHOD Reynolds-averaged Navier–Stokes equations Transonic |
| Zdroj: | Aerospace Science and Technology Aerospace Science and Technology, Elsevier, 2018, 76, pp.484-496. ⟨10.1016/j.ast.2018.02.023⟩ |
| ISSN: | 1270-9638 |
| DOI: | 10.1016/j.ast.2018.02.023⟩ |
| Popis: | The paper presents a numerical framework for the aerodynamic analysis of aircraft wings in transonic cruise and take-off/landing compatible with preliminary and conceptual design phase requirements based on the Non-Linear Vortex Lattice Method (NL-VLM). The purpose of this work is to demonstrate the applicability of the VLM-2.5D RANS approach for aircraft design optimization. The algorithm captures wing sweep effects, important in the transonic regime and near C L m a x conditions, by a stripwise viscous-inviscid coupling strategy with an infinite-swept wing (2.5D) Reynolds-Averaged Navier–Stokes (RANS) solver. Aerodynamic forces are evaluated through spanwise integration of the 2.5D RANS solutions and a trefftz-plane analysis of the VLM solver. The framework allows calculations of single and multi-element configurations without modifying the VLM mesh. A novel C L m a x criteria is proposed based on recently observed stall-cells patterns that captures C L m a x , α m a x and the spanwise location of the stall, which represent important design parameters. The applicability of the framework to aircraft design is demonstrated by embedding the analysis tools into a gradient-free Covariance Matrix Adaptation Evolution Strategy. After a verification phase, validation is performed on high-speed, high-lift and combined high-speed/high-lift optimizations cases. In particular, the capability of the numerical algorithms towards multi-topology optimization is demonstrated. |
| Databáze: | OpenAIRE |
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