Download reduction on a three dimensional V-22 model using active flow control

R. Grife, A. Darabi, I. Wygnanski

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

15 Scopus citations


This study focuses on the use of active flow control to reduce hover download on a 10.5% scale V- 22 powered model. In hover mode, approximately 10% of the total thrust is lost due to drag on the airframe. Two sources of download were investigated: impingement of downwash onto the wing and the fountain flow between the rotors. The download from the wing and fountain contribute 58% and 17.5% of the download respectively1. Encouraged by the results of two-dimensional active flow control testing2,3, which indicated significant download reductions on the V-22 airfoil, similar configurations were constructed for test and evaluation on a complete three-dimensional model of the V-22. Download measurement showed that a 15% reduction in download could be achieved with an oscillatory jet injected into the flow on the upper flap surface. A preliminary investigation using threedimensional PIV was performed in an effort to better understand the tiltrotor flow characteristics. The PIV data indicates that semi-span tiltrotor testing with an image plane has major effects on the global flow.

Original languageEnglish (US)
Title of host publication1st Flow Control Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624101052
StatePublished - 2002
Event1st Flow Control Conference 2002 - St. Louis, MO, United States
Duration: Jun 24 2002Jun 26 2002

Publication series

Name1st Flow Control Conference


Other1st Flow Control Conference 2002
Country/TerritoryUnited States
CitySt. Louis, MO

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes
  • Aerospace Engineering
  • Control and Systems Engineering


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