Natural laminar-flow supercritical wing section applied to sweepback wing of intermediate range civil airplane

Abstract

The invention provides a natural laminar-flow supercritical wing section applied to a sweepback wing of an intermediate range civil airplane. The natural laminar-flow supercritical wing section has the following pressure distribution form: a bump appears in a front edge area of an upper surface, i.e., an area with a chordwise range of 0 to 5 percent C, a pressure coefficient height of the bump is 0.05, a bump area accounts for 0.3 percent of a whole pressure distribution area, which is used for inhibiting the unstable disturbance development of a three-dimensional cross-flow CF wave; and a favorable pressure gradient is kept in an area from the back of the bump to a shock wave position, which is used for inhibiting the unstable disturbance development from a two-dimensional flow to a TS wave. The natural laminar-flow supercritical wing section has the advantages that the development of the two-dimensional TS wave disturbance and the three-dimensional cross-flow CF wave disturbance can be simultaneously inhibited, the transition of boundary laminar flow occurring in the front edge area when the wing section is arranged on the sweepback wing can be avoided, so that a relatively large-scale natural laminar flow can still be maintained on the surface of the sweepback wing, the resistance of a whole airplane can be reduced, the cruise efficiency is increased, and the consumption of fuel oil and carbon dioxide discharging can be reduced.

Description

Technical field [0001] The invention belongs to the technical field of aerodynamics, and particularly relates to a natural laminar flow supercritical airfoil applied to the swept wing of a medium-range civil aircraft. Background technique [0002] Nowadays, the international community has higher and higher requirements for energy-saving and emission-reduction indicators for new passenger and transport aircraft (hereinafter referred to as civil aircraft). On the basis of existing designs, how to further reduce the resistance of civil aircraft, improve cruise efficiency, and thereby reduce fuel consumption and carbon dioxide emissions, becomes more and more important. At present, the use of natural laminar flow supercritical airfoil to achieve drag reduction design is one of the key technologies with great potential to achieve this goal. [0003] The design idea of ​​the traditional natural laminar flow supercritical airfoil is: use weak shock waves to form a sufficient pressure gra...

AI Technical Summary

Problems solved by technology

[0007] Aiming at the defects in the prior art, the present invention provides a natural laminar supercritical airfoil applied to the swept wing of a medium-range civil aircraft, which is used to solve the problem of the traditional natural laminar supercritical airfoil applied to the swept wing. At the same time, it is easy to induce a transition at the leading edge of the wing due to the unstable disturbance of the three-dimensional cross-flow CF wave, and it is difficult to maintain a large-scale natural laminar flow on the surface of the wing.

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