Flow studies around a small propeller in converting maneuver

Sergey Shkarayev, Vladimir Kurnosov, David Gomez, Thierry Jardin, Jean Marc Moschetta

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Scopus citations


This study addresses the aerodynamics of propellers used in small unmanned aerial vehicles (UAVs) during transition between two flight modes: forward-flight and near-hover. Wind tunnel experiments were conducted for two angles of attack. Velocity fields behind retreating and advancing blades were measured using Particle Image Velocimetry (PIV). The vortex center and the core boundary were accurately identified by the method based on the normalized angular momentum. The major difference in an advancing blade as compared to a retreating one is in a stronger downwash behind the advancing propeller pushing the entire wake downward. Slopes of vortex center lines for the advancing blade are about two times steeper than in the retreating one. Peaks of velocity components are located right behind the propeller plane. On the advancing blade side, the vertical velocity component is approximately two times greater than on the retreating blade side. An increase in the vortex core size with the distance traveled is observed.

Original languageEnglish (US)
Title of host publication35th AIAA Applied Aerodynamics Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105012
StatePublished - 2017
Event35th AIAA Applied Aerodynamics Conference, 2017 - Denver, United States
Duration: Jun 5 2017Jun 9 2017

Publication series

Name35th AIAA Applied Aerodynamics Conference, 2017


Other35th AIAA Applied Aerodynamics Conference, 2017
Country/TerritoryUnited States


  • Blade
  • PIV
  • Propeller
  • Velocity
  • Vortex
  • Wind tunnel

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering


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