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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).
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2 Converging-diverging nozzles, redundancy. 1 comment. 3 Supercritical airfoil Mach Number ... 6 This article is about what is good about these wings. 1 comment ...
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 ...
Vortilons can be seen projecting from underneath the center leading edge of the wings of this Hawker 850XP. Vortilons are fixed aerodynamic devices on aircraft wings used to improve handling at low speeds. [1] [2] The vortilon was invented [3] by aerodynamicists working at Douglas Aircraft who had previously developed the engine pylons for the ...
Anti-shock body is the name given by Richard T. Whitcomb to a pod positioned on the upper surface of a wing. [1] Its purpose is to reduce wave drag while travelling at transonic speeds (Mach 0.8–1.0), which includes the typical cruising range of conventional jet airliners.
Clark Y is the name of a particular airfoil profile, widely used in general purpose aircraft designs, and much studied in aerodynamics over the years. The profile was designed in 1922 by Virginius E. Clark using thickness distribution of the German-developed Goettingen 398 airfoil. [1]
After World War II, NACA research began to focus on near-sonic and low-supersonic airflow.After considering the sudden drag increase which a wing-fuselage combination experiences at somewhere around 500 mph (800 km/h), Whitcomb concluded that "the disturbances and shock waves are simply a function of the longitudinal variation of the cross-sectional area" – that is, the effect of the wings ...
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