![]() However, for root-mean square pressure distribution, numerical results are higher than the experimental data in the trailing edge region. Comparing uncertainty bounds with experimental data, numerical results are reliable to predict the reduced frequency and mean pressure distribution. A supercritical airfoil is computationally tested at 2 and 10 turbulence intensity levels, Mach 0.8 and Mach 0.9 at 0 0 and 5 0 AoA. It is shown that the most sensitive part of flow to uncertain parameters is near the shock wave motion region. Since the supercritical pressure distribution of airfoil. Most combinations of the free stream conditions and airfoil maximum thickness are covered. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers. This report summarizes the supercritical airfoil development program in a chronological fashion, dis- cusses some of the design guidelines, and presents coordinates of a matrix of family-related super- critical airfoils with thicknesses from 2 to 18 percent and design lift coefficients from 0 to 1.0. Click on an airfoil image to display a larger preview picture. They are often used for civil aircraft designs. Airfoil database search (NACA 4 digit) Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Furthermore, mean pressure distribution and root-mean square pressure distribution from the upper surface are displayed with uncertainty bounds containing 95% of all possible values. The single shock wave supercritical airfoils usually have more robust and balanced performance in both cruise condition and off-design conditions. To represent the stochastic solution, the mean and standard deviation of variation of flow quantities such as lift and drag coefficients are computed. The calculator below can be used to plot and extract airfoil coordinates for any NACA 4-series airfoil. ![]() The effects of the uncertainties on lift, drag, mean pressure and root-mean square pressure are discussed. Supercritical airfoils are designed to delay and reduce the transonic drag rise, due to both strong normal shock and shock-induced boundary layer separation. ![]() Distributions of uncertain parameters are established according to the NASA wind tunnel report. To improve the predictive ability of computational fluid dynamics (CFD) on the transonic buffet phenomenon, NASA SC(2)-0714 supercritical airfoil is numerically investigated by noninstructive probabilistic collocation method for uncertainty quantification. ![]()
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