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Experimental research on Aerodynamic Performance of an USPLSC airfoil

Author Affiliations

  • 1School of Aeronautics, Northwestern Polytechnical University, Xi`an, China

Res. J. Engineering Sci., Volume 5, Issue (5), Pages 20-30, May,26 (2016)


Fre-and-aft symmetrical upper surface protrude lower surface concave (USPLSC) airfoils have been developed for the coaxial rotating wing of an UAV. In order to understand the aerodynamical performance of the airfoil, low speed wind tunnel experiment is carried out to measure lift coefficient, drag coefficient and pressure distribution under wind speed 20~40 m/s. Results are compared with CFD prediction using Fluent software. A satisfied agreement has been achieved and error analysis is provided. The purpose of this study is to conduct a parametric investigation on the performance of USPLSC airfoils for coaxial rotating wing UAV. The main objective of this study is to test USPLSC in wind tunnel and compare the experiment result with CFD simulation result.


  1. Gordon Leishman J. (2000)., Principles of Helicopter Aerodynamics with CD Extra., Cambridge University Press, New York, 1-4. ISBN: 987-0-521-66060-0.
  2. Colin P. Coleman. (1997)., A survey of theoretical and experimental coaxial rotoraero dynamic research., Ames Research Center, Moffett Field, California. 0704-0188
  3. John D. Anderson Jr. (2005)., Fundamentals of aerodynamics., McGraw-Hill Education, ISBN-13: 978-0073398105
  4. Emami M.R. (2007)., Aerodynamic forces on an airfoil., AER 303F, Aerospace Laboratory I. University of Toronto, Toronto.
  5. Chow C.Y. (1979)., An introduction to computational fluid dynamics., John Wiley and Sons, Inc.,New York, NY
  6. FLUENT 6.3. (2006)., User Guide, FLUENT Inc. of American.
  7. GAMBIT 6.2. (2006)., User Guide, FLUENT Inc. of American.