NGHIÊN CỨU ĐẶC TÍNH KHÍ ĐỘNG CÁNH HAI TẦNG DẠNG BUSEMANN CÓ CÁNH TÀ TẠI VẬN TỐC DƯỚI ÂM=INVESTIGATION OF AERODYNAMIC CHARACTERISTICS OF BUSEMANN AIRFOIL INCORPORATING A FLAP AND SLAT IN LOW-SPEED FLOW

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Tác giả: Thái Dương Nguyễn, Thế Hùng Trần

Ngôn ngữ: vie

Ký hiệu phân loại:

Thông tin xuất bản: Journal of Science and Technique, 2025

Mô tả vật lý: tr.53

Bộ sưu tập: Báo, Tạp chí

ID: 486726

Thêm vào giỏ

Cánh hai tầng dạng Busemann có thiết kế đặc biệt với khoảng cách giữa hai tầng cánh được tính toán nhằm tận dụng hiệu ứng giao thoa và triệt tiêu sóng xung kích, giúp giảm lực cản và tiếng nổ khi bay với tốc độ siêu âm. Ở tốc độ thấp, do cấu trúc cánh mỏng nên khi cất và hạ cánh, lực nâng của cánh còn hạn chế. Các nghiên cứu được thực hiện nhằm cải thiện tính năng cất, hạ cánh của cánh Busemann ở vận tốc dưới âm bằng các thiết bị tăng lực nâng, trong đó có cánh tà. Trong nghiên cứu này, ảnh hưởng của cánh tà đến đặc tính khí động tại vận tốc dưới âm của cánh hai tầng Busemann được phân tích thông qua thực nghiệm và mô phỏng số. Mô hình kết hợp cánh tà trước và cánh tà sau được thiết kế với khoảng cách gập tại vị trí 0,3 lần dây cung từ trước và sau đuôi cánh, góc lệch của cánh tà trước là 15°, góc lệch của cánh tà sau là 30°. Vận tốc dòng tới là 15 m/s, tương ứng với số Reynolds là 2,1·105. Khi kết hợp với cánh tà sau, tổng lực nâng và lực cản của cánh hai tầng Busemann tăng lên, hiện tượng thất tốc xuất hiện và hệ số lực nâng tối đa tăng hơn 1,3 lần so với cánh cơ bản, từ 1,6 lên hơn 2,15. Tỉ lệ đóng góp của cánh dưới phân bố vào tổng lực nâng và lực cản của cánh hai tầng giảm so với cánh cơ bản ở các góc tấn trên 0°. Cánh tà trước làm tăng độ dốc lực nâng và lực nâng tối đa, đáp ứng được yêu cầu về hệ số lực nâng cần thiết cho quá trình cất, hạ cánh. Cùng với đó, cánh tà trước làm giảm sự tách dòng trên bề mặt của cánh trên và cánh dưới, giúp giảm lực cản so với mô hình chỉ có cánh tà.The Busemann biplane wing employs a unique design, with inter-wing spacing optimized to suppress shock wave formation and minimize drag and noise at supersonic speeds. However, the resulting thin profile leads to reduced lift, impacting takeoff and landing. The use of slats and flaps is a promising approach to enhance takeoff and landing performance. In this research, the low-speed aerodynamic characteristics of Busemann airfoil installed slat and flap are investigated. The slat and flap are configured with hinge points located at 0.3c from the leading and trailing edges. The slat and flap deflection angles are 15° and 30°, respectively. The experiments are performed at a freestream velocity of 15 m/s, corresponding to a Reynolds number of 2.1·105. Results showed that the model incorporating flaps led to increases in both total lift and drag. The maximum lift coefficient increased from 1.6 in the baseline configuration to over 2.15 with the deployed flaps, while the lift curve slope remained relatively unchanged. At positive angles of attack, the lower element's contribution to both total lift and drag diminished compared to the baseline model. The slats effectively increased the lift slope and maximum lift coefficient, fulfilling the lift coefficient requirements for takeoff and landing. Additionally, the slats mitigated flow separation on both the upper and lower element surfaces, resulting in a reduction in drag compared to the configuration with flaps only.

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