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Article summary:
1. Two main methods are currently used for the numerical simulation of the aerodynamic interaction flow field of rotor aircraft: the body-fitted grid method and the momentum source method.
2. The virtual blade method (VBM) is an improvement of the steady momentum source method, which does not need additional aerodynamic models and uses blade element theory combined with local velocity to calculate aerodynamic force.
3. The Ffowcs Williams and Hawkings (FW–H) equation is often employed in the calculation and analysis of helicopter rotor thickness and load noise.
Article analysis:
The article provides a comprehensive overview of current methods used for numerical simulation of the aerodynamic interaction flow field of rotor aircraft, as well as a detailed description of a new virtual blade method (VBM). The article is well-structured, clearly written, and provides sufficient evidence to support its claims. However, there are some potential biases that should be noted. For example, while the article mentions other methods such as body-fitted grid and momentum source methods, it focuses mainly on VBM without providing an equal amount of information about these other methods. Additionally, there is no discussion about possible risks associated with VBM or any counterarguments that could be made against it. Furthermore, there is no mention of any promotional content or partiality in favor of VBM over other methods. All in all, this article appears to be reliable and trustworthy overall but could benefit from more balanced coverage of different methods available for numerical simulation of rotor aircrafts' aerodynamic interaction flow field.