![]() Both the thickness distribution and the camber of the wing determine how much the air accelerates around the wing. Standard wing shapes are designed to create lower pressure over the top of the wing. Supercritical airfoils are characterized by their flattened upper surface, highly cambered ("downward-curved") aft section, and larger leading-edge radius compared with NACA 6-series laminar airfoil shapes. A supercritical airfoil (supercritical aerofoil in British English) is an airfoil designed primarily to delay the onset of wave drag in the transonic speed range.Le régime d'écoulement est alors transsonique. Le Mach critique est celui où, l'avion étant à une vitesse inférieure à celle du son, l'écoulement commence à devenir supersonique sur une partie du profil. La vitesse critique de l'avion est celle qui provoque localement un écoulement supersonique de l'air sur la partie supérieure de l'aile et induit une trainée d'onde. Une voilure supercritique est en aéronautique un profil d'aile dont la vitesse critique est plus grande que pour une voilure conventionnelle.This article is distributed under the terms of the Creative Commons Attribution 4.0 International License ( ), which permits unrestricted use, distribution, and reproduction in any medium, provided you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license, and indicate if changes were made. The effects of sidewall boundary in two-dimensional subsonic and transonic wind tunnels. Comparison of computational and experimental results for a supercritical airfoil. ![]() National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, Washington, D.C., NASA TP-2890. NASA SC(2)-0714 Airfoil Data Corrected for Sidewall Boundary-layer Effects in the Langley 0.3-meter Transonic Cryogenic Tunnel. Reynolds number effect investigation of supercritical airfoil based on wind tunnel test. Transonic unsteady pressure measurements on a supercritical airfoil at high Reynolds numbers. Correlation of data related to shock-induced trailing-edge separation and extrapolation to flight Reynolds number. Similarity rules for sidewall boundary-layer effect in two-dimensional wind tunnels. Design and performance evaluation of slotted walls for two-dimensional wind tunnels. Keywords:ĬFD, correlation, EFD, supercritical airfoil,īarnwell, R., 1978. The correlation of EFD and CFD improved after the correction of EFD results and validation of CFD method. The CFD method is validated and the Barnwell-Sewell method is feasible for sidewall effects correction. It is shown that there was large disparity between CFD and uncorrected EFD results, while CFD and EFD compared well after correction. The Barnwell-Sewell method is applied to correct sidewall effects for experimental results of typical supercritical airfoil CH obtained in NF-6 wind tunnel. In this study, NASA SC (2) -0714 airfoil is numerically simulated and compared with NASA corrected experimental results to validate the CFD method. ![]() It is necessary to improve the correlation between CFD and EFD through the correction of EFD results and validation of CFD method, thus investigating the aerodynamic characteristics of supercritical airfoil perfectly.
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