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Supercritical airfoil database3/19/2024 It was shown that extrapolated result compared well with simulated result at Reynolds number 30×10 6, implying that the engineering method was at least promising applying to the extrapolation of low Reynolds number wind tunnel data. The calculator below can be used to plot and extract airfoil coordinates for any NACA 4-series airfoil. Based on the similar parameter, airfoil pressure distribution at Reynolds number 30×10 6 was obtained by extrapolation. A similar parameter describing the Reynolds number effects factors was obtained by analyzing the relationship of shock wave location, shock front pressure and trailing edge pressure. Simulated results indicated that weak shock existed on the upper surface of supercritical airfoil at cruise condition, that the shock location, shock strength and trailing edge pressure were dependent of Reynolds number, attack angles and Mach numbers. The supercritical airfoil pressure distribution were obtained with Reynolds numbers varied from 3.0×10 6 to 30×10 6 per airfoil chord, angles of attack from 0 degree to 6 degree and Mach numbers from 0.74 to 0.8. Influence of computational grids convergence and turbulent models were investigated during the process of simulation. Flows over a typical supercritical airfoil were numerically simulated by solving the two dimensional Navier-Stokes equations, with applications of ROE scheme spatial discretization and LU-SGS time march. Correlation screening and multivariate regression are carried out to discover knowledge about the airfoil drag divergence Mach number and pressure. However, the extrapolation method requiring plenty of data was investigated based on the CFD results for the reason of low cost and short period. This paper generates a supercritical airfoil database that covers the typical free stream Mach number, angle of attack, lift coefficient, and geometry of modern transonic commercial aircraft. A: A supercritical airfoil is a special airfoil designed to reduce the drag when operating near supersonic speeds. This paper aimed to explore an engineering extrapolation to flight Reynolds number from low Reynolds number wind tunnel data for supercritical airfoil pressure distribution. Pressure distribution of supercritical airfoil at flight Reynolds number could not be fully simulated except in cryogenic wind tunnel such as NTF (National Transonic Facility) and ETW (European Transonic Wind tunnel), which is costly and time resuming.
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