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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).
3 Supercritical airfoil Mach Number/pressure coefficient diagram. ... 6 This article is about what is good about these wings. 1 comment. Toggle the table of contents.
A shock stall is a stall created when the airflow over an aircraft's wings is disturbed by shock waves formed when flying at or above the aircraft's drag divergence Mach number. Shock stall may cause control problem during speed transition (transonic to supersonic). Thin supercritical wing section and swept-back wing can postpone shock stall to ...
Experimental Vought F-8 Crusader with supercritical wing. The supercritical wing would have been prone to pitch-up as the wing had increased sweep and aspect ratio compared to the standard wing. No pitch-up problems were experienced with vortilons fitted. [14] [15] Bombardier Challenger 300, later becoming the Challenger 350 & new 3500 series.
The NACA four-digit wing sections define the profile by: [2] First digit describing maximum camber as percentage of the chord. Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord. Last two digits describing maximum thickness of the airfoil as percent of the chord. [3]
A supercritical fluid (SCF) is a substance at a temperature and pressure above its critical point, where distinct liquid and gas phases do not exist, ...
Years of research and experience with the unusual conditions of supersonic flow have led to some interesting conclusions about airfoil design. Considering a rectangular wing, the pressure at a point P with coordinates (x,y) on the wing is defined only by the pressure disturbances originated at points within the upstream Mach cone emanating from point P. [3] As result, the wing tips modify the ...
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