Compressibility effects on airfoil aerodynamics at low Reynolds number

Tetsuya Suwa, Kei Nose, Daiju Numata, Hiroki Nagai, Keisuke Asai

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

4 Citations (Scopus)

Abstract

The objective of this study is to clarify the Mach number effect on the aerodynamic characteristics of airfoils at low Reynolds number. In this study, we conducted airfoil tests using a flat plate and a triangular airfoil in the Mars Wind Tunnel at Tohoku University. Reynolds number was set at 3,000 and 10,000 and Mach number at 0.15, 0.5 and 0.7. Aerodynamic force and pressure distributions on the models were measured using a force balance and Pressure-Sensitive Paint (PSP). The results show that the compressibility effect has an effect to move the flow separation point backward and to delay a reattachment of separated shear layer on the airfoil. These effects reduce the lift and the maximum lift-drag ratio.

Original languageEnglish
Title of host publication30th AIAA Applied Aerodynamics Conference 2012
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
Pages1571-1583
Number of pages13
ISBN (Print)9781624101854
DOIs
Publication statusPublished - 2012 Jan 1
Event30th AIAA Applied Aerodynamics Conference 2012 - New Orleans, LA, United States
Duration: 2012 Jun 252012 Jun 28

Publication series

Name30th AIAA Applied Aerodynamics Conference 2012

Other

Other30th AIAA Applied Aerodynamics Conference 2012
CountryUnited States
CityNew Orleans, LA
Period12/6/2512/6/28

ASJC Scopus subject areas

  • Aerospace Engineering

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  • Cite this

    Suwa, T., Nose, K., Numata, D., Nagai, H., & Asai, K. (2012). Compressibility effects on airfoil aerodynamics at low Reynolds number. In 30th AIAA Applied Aerodynamics Conference 2012 (pp. 1571-1583). (30th AIAA Applied Aerodynamics Conference 2012). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2012-3029