Effect of camber on the aerodynamics of adaptive wing micro air vehicles

W. Null, S. Shkarayev

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

6 Scopus citations

Abstract

Four micro air vehicle wind tunnel models were built with 3, 6, 9 and 12% camber, all based upon the S5010-TOP24C-REF thin, cambered plate airfoil. These models were tested in the Low Speed Wind Tunnel at angles of attack ranging from 0 to 35° and velocities of 5, 7.5 and 10 m/s, corresponding to chord Reynolds numbers of 5x104, 7.5x104 and 1x105, respectively. CL, CD, CM and L/D were obtained and plotted versus angle of attack for all the cambers at each velocity. Large positive, nose-up pitching moment coefficients were found with all cambers at the lowest Reynolds number. These results have been verified with flight tests of micro air vehicles utilizing these airfoils. The 3% camber wing gives the best lift-to-drag ratio of the four cambers and theoretically would be the optimal choice for high speed, efficient flight. It is theorized that the 9% camber wing will give the best low-speed performance due to its high lift-to-drag ratio and mild pitching moment near its stall angle of attack.

Original languageEnglish (US)
Title of host publication2nd AIAA Flow Control Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624100307
DOIs
StatePublished - 2004
Event2nd AIAA Flow Control Conference 2004 - Portland, OR, United States
Duration: Jun 28 2004Jul 1 2004

Publication series

Name2nd AIAA Flow Control Conference

Other

Other2nd AIAA Flow Control Conference 2004
CountryUnited States
CityPortland, OR
Period6/28/047/1/04

ASJC Scopus subject areas

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

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  • Cite this

    Null, W., & Shkarayev, S. (2004). Effect of camber on the aerodynamics of adaptive wing micro air vehicles. In 2nd AIAA Flow Control Conference (2nd AIAA Flow Control Conference). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2004-2694