科研之友
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摘要
This paper presents a numerical study of the transonic flow over a half wing-body configuration representative of a large civil aircraft. The Mach number is close to cruise conditions, whereas the high angle of attack causes strong separation on the suction side of the wing. Results indicate the presence of shock-wave oscillations inducing unsteady loads that can cause serious damage to the aircraft. Transonic shock buffet is found. Based on exploratory simulations using a baseline grid, the region relevant to the phenomenon is identified and mesh adaptation is applied to significantly refine the grid locally. Time-accurate Reynolds-averaged Navier-Stokes and delayed detached-eddy simulations are then performed on the adapted grid. Both types of simulation reproduce the unsteady flow physics, and much information can be extracted from the results when investigating frequency content, the location of unsteadiness, and its amplitude. Differences and similarities in the computational results are discussed in detail and are also analyzed phenomenally with respect to recent experimental data.
- 出版日期2017-4
