SIGNIFICANCE OF ALL-SPEED SCHEME IN APPLICATION TO ROTORCRAFT CFD SIMULATIONS
The flow speed around a helicopter has a wide variation from very low (M～0.1) to transonic (M～0.9) when full configuration and full flight regime are considered. Special care must be taken when CFD methods are applied to this problem. An all-speed numerical scheme, SLAU is utilized combined with an overlapped moving grid approach to simulate the flow field around a rotor with a fuselage model. A two-level discretization in time is used and solved implicitly with a dual-time stepping method ensuring accuracy in time when solving unsteady flows. Test cases from Caradonnas two-bladed hovering rotor experiments, HART II baseline case and ROBIN database are selected for the validation of the newly developed rotor simulation code (named rFlow3D). Stable convergences are obtained even at low rotor speed and low flight speed and good agreements are found between the experimental and CFD results. These are considered mainly benefit from the utilization of all-speed scheme.
Yasutada Tanabe Shigeru Saito
Helicopter Technology Section Aviation Program Group Japan Aerospace Exploration Agency, Jindaiji-Higashi-Machi 7-44-1, Chofu, Tokyo, 182-8522, Japan
国际会议
南京
英文
1-8
2009-10-14（万方平台首次上网日期，不代表论文的发表时间）