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2. Supercritical airfoil - Wikipedia

   en.wikipedia.org/wiki/Supercritical_airfoil

   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. Talk:Supercritical airfoil/Archive 1 - Wikipedia

   en.wikipedia.org/wiki/Talk:Supercritical_airfoil/...

   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 ...

4. NACA airfoil - Wikipedia

   en.wikipedia.org/wiki/NACA_airfoil

   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]

5. Drag-divergence Mach number - Wikipedia

   en.wikipedia.org/wiki/Drag-divergence_Mach_number

   Two of the important technological advancements that arose out of attempts to conquer the sound barrier were the Whitcomb area rule and the supercritical airfoil. A supercritical airfoil is shaped specifically to make the drag-divergence Mach number as high as possible, allowing aircraft to fly with relatively lower drag at high subsonic and ...

6. Shock stall - Wikipedia

   en.wikipedia.org/wiki/Shock_stall

   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 ...

7. Supersonic airfoils - Wikipedia

   en.wikipedia.org/wiki/Supersonic_airfoils

   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 ...

8. Richard T. Whitcomb - Wikipedia

   en.wikipedia.org/wiki/Richard_T._Whitcomb

   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 ...

9. Clark Y airfoil - Wikipedia

   en.wikipedia.org/wiki/Clark_Y_airfoil

   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]