Abstract: In the preliminary design stage of the aircraft, it is very important to obtain true and accurate aerodynamic characteristics for the improvement and finalization of the aircraft design process. However, the current scaled model wind tunnel tests used at the initial stage of the design have their own limitations and the predicted aerodynamic data are not always consistent with the real flight conditions, with the Reynolds number effect being one of the main causes of this discrepancy. In this paper, CFD numerical simulation method is used to analyze the two configurations of the flight verification platform with and without the high-lift device opening under test and flight Reynolds number, respectively. The reliability and accuracy of the numerical simulation results are verified by comparing the calculated aerodynamic coefficients with the wind tunnel test data, which also supports the validity of the wind tunnel results. And the comparisons of the calculated aerodynamic coefficients at low and high speed conditions, the transition location on the upper surface of the laminar wing section and the results of the flow field are further proposed to clarify the specific effects of Reynolds number on three key aspects of the verification platform with special layout, including the aerodynamic performance, the low-speed stall characteristics and the high-speed laminar transition characteristics. The results and laws obtained from the above tests, calculations and analysis can be used for the correction of the Reynolds number effects and provide sufficient data to support the design of the later flight tests.

Key words: flight verification platform, Reynolds number effect, laminar wing, wind tunnel test, aerodynamic performance