Furthermore, it enables the cruise performance and drag divergence Mach number to be predicted with only one simulation of the cruise point, which will greatly save the computational cost of optimizations. It indicates that the drag divergence Mach number can be increased by obtaining a shock wave that is further upstream in the detailed design. Compared with Korn's equation, the discovered correlation reduces the maximum prediction error by approximately 40%. Source UIUC Airfoil Coordinates Database. A new linear correlation is discovered and validated by existed airfoil databases. (lrn1015-il) NASA LRN 1015 (NASA TM 102840) LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil. Correlation screening and multivariate regression are carried out to discover knowledge about the airfoil drag divergence Mach number and pressure distribution features. This paper designs a supercritical airfoil database that covers the typical free stream Mach number, angle of attack, lift coefficient, and geometry of modern transonic commercial aircraft. However, it neither reveals the key factors of fluid features on the drag divergence nor contributes to the detailed design. It is very helpful in the aircraft initial design. For example, Korn's equation predicts the airfoil drag divergence Mach number using the airfoil maximum thickness and the lift coefficient. The NASA data set comprises different size NACA 0012 airfoils at various wind tunnel speeds and angles of attack. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers. Click on an airfoil image to display a larger preview picture. Aerodynamic rules and knowledge are often obtained through theoretical research and experiments, which have contributed greatly to aircraft design. Airfoil database search (NACA 4 digit) Search the 1638 airfoils available in the databases filtering by name, thickness and camber.
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