Abstract
Optimization design was widely used in the high-lift device design process, and the aeroacoustic reduction characteristic is an important objective of the optimization. The aerodynamic and aeroacoustic study on the baseline wing and flap configuration was performed numerically. In the current study, the three-dimensional Large Eddy Simulation (LES) equations coupled with dynamic Smagorinsky subgrid model and Ffowcs–William and Hawkings (FW–H) equation are employed to simulate the flow fields and carry out acoustic analogy. The numerical results show reasonable agreement with the experimental data. Further, the particle swarm optimization algorithm coupled with the Kriging surrogate model was employed to determine optimum location of the flap deposition. The Latin hypercube method is used for the generation of initial samples for optimization. In addition, the relationship between the design variables and the objective functions are obtained using the optimization sample points. The optimized maximum overall sound pressure level (OASPL) of far-field noise decreases by 3.99 dB with a loss of lift-drag ratio (L/D) of less than 1%. Meanwhile, the optimized performances are in good and reasonable agreement with the numerical predictions. The findings provide suggestions for the low-noise and high-lift configuration design and application in high-lift devices.
Highlights
With the rapid development of civil aviation, aeroacoustic problems were of wide concern among aviation manufacturing enterprises and researchers the world over
The results showed that unsteady flow phenomena such as vortex shedding and flow separation can be accurately captured by Large Eddy Simulation (LES) method, and the acoustic analogy method based on Ffowcs–William and Hawkings (FW–H) can accurately and efficiently solve the far-field aerodynamic noise
The particle swarm optimization algorithm combined with Kriging surrogate model is applied to optimize the flap position parameters of three-dimensional wing and flap configuration
Summary
With the rapid development of civil aviation, aeroacoustic problems were of wide concern among aviation manufacturing enterprises and researchers the world over. During takeoff and landing of civil aircraft, the flap lifting device is one of the main components that produce noise [3]. In the noise generated by flap lifting device, the side edge vortex shedding of the flap is the main noise source [4]. The research on the flap side edge noise source can be traced back to 1979, when Fink [5] and Schlinker [6] found that the flap side edge was an important aircraft noise source. Khorrami et al [8] analyzed and showed that the unstable wave in the lateral shear layer is the main cause of noise by using the instability theory
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
