A high-drag divergent Mach number laminar airfoil suitable for light-medium-sized high-speed business jets

Through the parameterized design and CFD analysis based on the RAE2822 airfoil, a high-resistance divergent Mach number laminar flow airfoil suitable for light and medium-sized high-speed business jets is proposed, which solves the problems of increased shock resistance and insufficient lift coefficient in the prior art, and achieves efficient aerodynamic performance.

CN114684348BActive Publication Date: 2025-03-18NORTHWESTERN POLYTECHNICAL UNIV
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Patent Information

Application Number
CN202210348656.7
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2022-04-01
Publication Date
2025-03-18
Estimated Expiration
2042-04-01

AI Technical Summary

Technical Problem

It is difficult to design airfoils suitable for light and medium-sized high-speed turbofan business jets, especially when meeting high speed, low drag divergence Mach number and low speed aerodynamic performance, there are problems of increased shock wave resistance and insufficient lift coefficient.

Method used

Based on the RAE2822 airfoil, a high-resistance divergent Mach number laminar flow airfoil is calculated, compared and analyzed by parameterization method and CFD method, and a high-resistance divergent Mach number laminar flow airfoil is proposed. The specific parameters include the leading edge radius, maximum thickness position, maximum curvature position, etc., and the parameterization formula and geometric coordinate expression of the upper and lower arcs are provided.

Benefits of technology

The Mach number of divergent resistance in high-speed cruising state reaches 0.73, the maximum lift coefficient of low-speed reaches 1.867, and the stall angle of attack increases to 17 degrees, meeting the requirements of design indicators, and improving the overall aerodynamic performance of the airfoil.

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Abstract

The invention provides a high-drag divergent Mach number laminar airfoil suitable for light-medium-sized high-speed business jets, wherein the airfoil is composed of a leading edge, a trailing edge, and an upper camber and a lower camber located between the leading edge and the trailing edge; the ratio of the leading edge radius r to the airfoil chord length c is r / c=1.47%, the ratio of the maximum thickness a to the airfoil chord length c is a / c=11.93%, the maximum thickness position is located at x / c=37.47%, the ratio of the maximum camber b to the airfoil chord length c is b / c=1.17%, the maximum camber position is The position is x / c=60.3%, the ratio of the trailing edge thickness w to the airfoil chord length c is w / c=0.146%; x is the distance from the leading edge to the trailing edge along the airfoil chord direction, and the values ​​of r / c, a / c, b / c, x / c and w / c have a maximum error of ±3% respectively; the lengths of the laminar flow areas on the upper and lower surfaces of the airfoil are not less than 40% of the chord length; when Ma=0.71, the airfoil drag divergence Mach number is not less than 0.73; when Ma=0.20, the airfoil maximum lift coefficient is not less than 1.75. The present invention is designed for laminar control in low-speed and high-speed cruising states, and has the characteristics of high lift, high lift-to-drag ratio, mild stall characteristics, and high drag divergence Mach number.
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