The dual-time implicit scheme is applied to simulate the unsteady flowfield on the movement grids. In the non-lift forward flight case, the total rotor is simulated in inertia coordinate system and the whole grid moves rigidly. In hover case only one rotor is simulated with the periodic boundary condition in the rotational coordinate system and the grid is fixed. The helicopter rotor field is simulated in hover and forward flight based on Computational Fluid Dynamics(CFD). The sound pressure level is estimated for different rotor blade collectives and observation angles.įlowfield analysis of helicopter rotor in hover and forward flight based on CFD The main rotor of the UH-1H helicopter is considered as a test case for comparison to experimental data. Farfield noise at a remote observer position is calculated at post processing stage using FW–H solver implemented in Fluent and HMB.
![realflight 7.5 helo hover trainer realflight 7.5 helo hover trainer](https://cdn11.bigcommerce.com/s-q0oivn9r3h/images/stencil/1280x1280/products/2671/3196/GPMZ4520-8__46778.1562597688.jpg)
Farfield observers are used and the nearfield flow parameters are obtained using the in house HMB and commercial Fluent CFD codes (identical hexa-grids are used for both solvers. The sound pressure level is estimated for different rotor blade collectives and observation angles.ĭirectory of Open Access Journals (Sweden)įull Text Available In this work rotor aeroacoustics in hover is considered.
![realflight 7.5 helo hover trainer realflight 7.5 helo hover trainer](https://cdn.cloudflare.steamstatic.com/steam/apps/1314820/ss_6868218de5df60c07e781797d3dacb5019f048ef.1920x1080.jpg)
Farfield noise at a remote observer position is calculated at post processing stage using FW-H solver implemented in Fluent and HMB. Farfield observers are used and the nearfield flow parameters are obtained using the in house HMB and commercial Fluent CFD codes (identical hexa-grids are used for both solvers).
![realflight 7.5 helo hover trainer realflight 7.5 helo hover trainer](https://cdn11.bigcommerce.com/s-q0oivn9r3h/images/stencil/1280x1280/products/2671/3195/GPMZ4520-7__80708.1562597687.jpg)
In this work rotor aeroacoustics in hover is considered. CAA modeling of helicopter main rotor in hover