Notice of Removal: A Numerical Approach to Investigating Parameter Effect on Aeroacoustic Performance of Helicopter Ducted Tail

Aircraft noise emission is continuously growing in importance owing to increasing strict airworthiness standers. For helicopter, ducted tail rotor is gaining interest for designers owing to its numerous advantages both in aerodynamic and aeroacoustic performance. The present work proposes an approach to investigating the effect of different structure parameters on the performance of ducted tail rotor, based on unsteady flow field computation results. The parameter effect on performance of ducted tail rotor is investigated numerically using incompressible detached eddy simulation and finite element acoustic analogy method. This approach promotes the complex ducted tail designs. The numerical prediction of prototype is verified by a comparison with acoustic wind tunnel experimental data. It is found that the proposed method of acoustic analogy is rather desirable comparing the experimental results. Several design parameters are modified to discuss the aerodynamic and acoustic performance. The results demonstrate the effectiveness of parameters modification of ducted tail rotor in aerodynamic and acoustic performance improvement.