Aerodynamic Performance of a Hovering Microrotor in Confined Environment

Abstract

This paper aims at understanding how the aerodynamic performance of a hovering microrotor is affected by horizontal and vertical wall proximity. Toward that end, experiments are performed to extract aerodynamic loads and velocity flow fields from strain gauges and high-definition stereoscopic particle image velocimetry measurements, respectively. The results show that horizontal wall boundary conditions contribute to enhancing aerodynamic performance, whereas vertical boundary conditions have a negligible impact. Enhancement of aerodynamic performance arises from distinct flow physics, such as rotor wake expansion or Venturi effects, that depend on the configuration considered. These results open the path toward the development of micro air vehicles dedicated to the exploration of highly confined environments.

Aerodynamic analysis and control for a novel coaxial ducted fan aerial robot in ground effect

“…The form of the fitting model is a  ðz=RÞ Àb þ c, and it is similar to Han et al 22 and Jardin et al 23 Analysis of flow field mechanism for ground effect…”

Fluid–Structure Interactions and Unsteady Kinematics of a Low-Reynolds-Number Rotor

“…6 for two configurations: 1) the reference configuration (pure rotation), and 2) a case where a forced motion of pitching is superimposed to the rotational speed (ω m 3Ω and q m 0.1724, corresponding to a variation of 9.9 deg around the average pitch angle). Experimental data for the reference configuration (pure rotation) have been obtained in the frame of a previous campaign [30]. Three different blade angles are considered for the LES-LBM: θ 10 deg, θ 15 deg, and θ 20 deg.…”

Rotor performance enhancement through blade surging

“…Results for constant rotation speed cases are compared with available experimental data obtained at a Reynolds number of 60,000 (see Jardin et al 10 for details on the experimental approach). Figure 2 shows that experimental data match the mean rotation torque Q versus mean thrust T curve computed using the present numerical approach within reasonable accuracy.…”