Comparative Study of BGK No. 1 Airfoil Data in High Reynolds Number TransonicWind Tunnels

摘要

A comparative study of BGK Number 1 airfoil data, in the National AerospaceLaboratory (NAL) in Japan and the Institute for Aerospace Research (IAR) in Canada, high Reynolds number transonic wind tunnels was performed to evaluate the techniques and the accuracy of airfoil testing. Tests were conducted from a low subsonic speed over the design speed of the airfoil mainly at a Reynolds number of 21 million based on airfoil chord at both facilities. Pressure distributions and aerodynamic characteristics measured in both wind tunnels are compared and discussed. The results of the comparisons reveal slight differences in shock position and suction peak level ahead of the shock, suggesting the necessity of a correction for sidewall boundary-layer effects. The results also raise new issues on drag measurement and flow two-dimensionality at a high angle of attack and/or a high Mach number. The results of this study will lead to improvements in the accuracy of airfoil testing.