Abstract
The efficiency and accuracy of numerical simulation on power unit is the key to study the relevant aerodynamic layout with multiple rotating power units. However, the numerical simulation of the power unit using real geometry all faces the problem of low solution efficiency. Taking the rotor hovering state as an example, the real blade was firstly simplified and replaced by a thin mesh disk to establish the effective momentum source method. Then, using fan-shaped mesh region that changes with time to replace real blade and simulate the rotation, the unsteady momentum source method which could get the revolution of tip vortex was proposed. The results show that the momentum source method with the input of accurate blade force distribution can simulate rotor wake better, and the influence that blade geometry acts on wake mainly reflects in the blade force distribution. In addition, the unsteady momentum source method can simulate the revolution of tip vortex, and its consumptions of computing resources and calculation time are only about 1/8 of the unsteady numerical simulation based on the real geometry.
Highlights
动量源法多采用定常计算的方式,但定常计算 并不能模拟出桨叶真实旋转下的非定常特征。 为解 决这一问题,并发挥动量源法计算高效的特点,非定 常动量源法 ( unsteady momentum source method, UMSM) 被提出。
Aerodynamic Analysis and Optimal Design of Tilt⁃Rotor Aircraft Based on an Unsteady Momentum Source Method [ D]
The numerical simulation of the power unit using real geometry all faces the problem of low solution efficiency
Summary
动量源法多采用定常计算的方式,但定常计算 并不能模拟出桨叶真实旋转下的非定常特征。 为解 决这一问题,并发挥动量源法计算高效的特点,非定 常动量源法 ( unsteady momentum source method, UMSM) 被提出。 Kim 及 Guntupalli 提出的非定常动量源法均耦 合叶素理论求解桨叶力分布,且均采用固定的桨盘 网格,如图 8 所示。 采用 f 分布,扭矩均分,命名为 UMSM- f; 2) 取周向 5 个网格的扇形区域代替桨叶,拉 力、扭矩均采用均分方式,命名为 UMSM- 5; 3) 取周向 2 个网格的扇形区域代替桨叶,拉
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
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
