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Supercritical airfoils feature four main benefits: they have a higher drag-divergence Mach number, [21] they develop shock waves farther aft than traditional airfoils, [22] they greatly reduce shock-induced boundary layer separation, and their geometry allows more efficient wing design (e.g., a thicker wing and/or reduced wing sweep, each of which may allow a lighter wing).
Precision Castparts Corp. is an American industrial goods and metal fabrication company that manufactures investment castings, forged components, and airfoil castings for use in the aerospace, industrial gas turbine, and defense industries. In 2009 it ranked 362nd on the Fortune 500 list, and 11th in the aerospace and defense industry. [3]
Design of the Gulfstream III started with an effort to synthesize a completely new wing employing NASA supercritical airfoil sections and winglets. Optimization studies considering weight, drag, fuel volume, cost, and performance indicated that a substantial portion of the new wing benefit could be secured with modifications to the existing wing.
Richard Whitcomb (1921–2009) – NACA/NASA inventor of the area rule, supercritical airfoil, and winglet; Ed White (1930–1967) – Apollo 1 fire victim on January 27, 1967; Gustave Whitehead (1874–1927) – aviation pioneer; Frank Whittle (1907–1996) – pioneer of the jet engine; Michel Wibault (1897–1963) – invented vectored thrust
It addition, the wing was a new design, with a higher aspect ratio and supercritical airfoil. It was designed to compete with the Airbus A310 and Boeing 767, developed in the same era and of similar size. McDonnell Douglas worked with NASA on the aerodynamic design, and wind tunnel testing was conducted. [1]
, is the coefficient of lift of a specific section of the airfoil, t is the airfoil thickness at a given section, c is the chord length at a given section, is a factor established through CFD analysis: K = 0.87 for conventional airfoils (6 series), [4] K = 0.95 for supercritical airfoils.
China's Ministry of Commerce said it would impose measures on 28 U.S. entities and would also prohibit exports of dual-use items to the listed companies starting on Thursday, reported the Global ...
For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.