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

R. Grife, A. Darabi, Israel J Wygnanski

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

12 Scopus citations

Abstract

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
Publication statusPublished - 2002
Event1st Flow Control Conference 2002 - St. Louis, MO, United States
Duration: Jun 24 2002Jun 26 2002

Other

Other1st Flow Control Conference 2002
CountryUnited States
CitySt. Louis, MO
Period6/24/026/26/02

    Fingerprint

ASJC Scopus subject areas

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

Cite this