Three-dimensional aerodynamic design method for back-supported engine nacelle

The companion optimization method for back-mounted engine short fuselage design addresses the complexity of wing-body fusion aircraft aerodynamics by parameterizing the geometry to match non-axisymmetric flows, achieving drag reduction and preventing flow separation, thereby enhancing both high-speed and low-speed flight performance.

CN119720367APending Publication Date: 2025-03-28AECC COMML AIRCRAFT ENGINE CO LTD
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Patent Information

Application Number
CN202311256756.8
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2023-09-26
Publication Date
2025-03-28

AI Technical Summary

Technical Problem

The design of back-mounted engine short fuselage for wing-body fusion aircraft faces challenges in optimizing three-dimensional aerodynamics due to numerous design variables and high computational complexity, particularly in achieving non-axisymmetric flow characteristics and reducing drag at both high-speed and low-speed flight conditions.

Method used

A three-dimensional aerodynamic design method using the companion optimization approach, which involves parameterizing the short fuselage geometry to match non-axisymmetric flow features, combining low-speed lip mouth design with companion gradient optimization for high-speed drag reduction, ensuring no flow separation at the inlet.

Benefits of technology

This method effectively reduces drag and prevents flow separation at the inlet, achieving significant drag reduction while efficiently handling the computational complexity of numerous design variables, thus optimizing both high-speed and low-speed flight performance.

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Abstract

The invention provides a three-dimensional aerodynamic design method of a back-supported engine nacelle, which is used for a wing-body fusion aircraft, adopts an accompanying optimization method, and comprises the following steps: S1, obtaining a prototype nacelle: obtaining three-dimensional geometric data of the prototype nacelle; s2, low-speed working condition nacelle design: aiming at a low-speed working condition, carrying out nacelle lip design which meets the requirement that flow separation does not occur in an air inlet channel; s3, nacelle design under the high-speed cruise working condition: carrying out three-dimensional aerodynamic design of a nacelle outer cover main body part by adopting the nacelle lip modeling designed in the step S2 and a method based on accompanying gradient optimization to obtain an optimized aerodynamic shape of the nacelle outer cover main body matched with a non-axisymmetric flow field in a mounting state; s4, low-speed working condition performance verification; and S5, optimization design termination judgment. According to the nacelle, the high-speed cruise working condition resistance of the wing body fusion aircraft back support engine is remarkably reduced, and meanwhile air inlet flow separation of the nacelle under the ground limit crosswind working condition is avoided.
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