Abstract:
The effects of Reynolds number on aerodynamic characteristics of large aircraft with supercritical wing are studied using wind tunnel test and numerical method. Based on the comparison and analysis between wind tunnel test results and numerical results, the latter are used in the correction of low Reynolds number test results for a high Reynolds number result. The corrected data are compared with the test data for the same Reynolds number. The differences of drag coefficient are less than 0.0004. The maximum difference of lift-drag ratio is approximately 0.2, and the differences of moment coefficient are less than 0.001.