| In the present work, a novel hybrid Euler-compressible vortex particle method is developed for 2-D transonic rotorcraft applications. It is identified that the advantages and disadvantages of traditional grid-based Euler/Navier-Stokes methods and those of vortex particle methods complement each other. This suggests that a hybrid approach, in which a grid-based Euler domain covering the near-field around the airfoil, coupled with a compressible vortex particle formulation representing the far-field, would be extremely beneficial to employ.;Validation of HEPM is performed in three phases. First, the convergence of the method is examined for steady flows at low and high Mach numbers and also for a rapidly sinusoidally pitching airfoil. Then, validation against experimental results is performed by comparisons to the AGARD CT6 and CT5 cases for ramped-up and sinusoidally pitching airfoils, respectively. Finally, airfoil-vortex interaction (AVI) studies are performed for an impinging vortex, with various vortex miss distances considered at both low and high Mach numbers. All of the above cases represent typical problems in rotorcraft aerodynamics.;This work focuses on two areas: firstly, a compressible vortex particle method (CVPM) formulation is developed. Then, the coupling of this method with an existing Euler solver (CMB) is completed, using a domain decomposition technique featuring complete overlap. This novel hybrid Euler-particle method is then designated as HEPM. |
