A Sonic Boom Suppression Method for Supersonic Aircraft Based on Blow and Suction Flow Control

A flow control and supersonic technology, applied in supersonic aircraft, aircraft parts, aircraft control, etc., can solve the adverse effects of aircraft aerodynamic performance, affect passenger ride experience and travel efficiency, etc., to meet the needs of supersonic flight, reduce sound Explosive strength, the effect of reducing resistance

Active Publication Date: 2021-10-15
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In addition, the congestion level of the future air traffic system will bring serious problems to travel: it is estimated that the passenger traffic will increase by 2 to 3 times in 2030, seriously affecting the passenger experience and travel efficiency
However, although the above method suppresses the sonic boom, it has an adverse effect on the aerodynamic performance of the aircraft.

Method used

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  • A Sonic Boom Suppression Method for Supersonic Aircraft Based on Blow and Suction Flow Control
  • A Sonic Boom Suppression Method for Supersonic Aircraft Based on Blow and Suction Flow Control
  • A Sonic Boom Suppression Method for Supersonic Aircraft Based on Blow and Suction Flow Control

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0101] Set two suction ports and two blow ports (configuration 1)

[0102] Step 1, determine the areas of compression and expansion of the lower surface of the aircraft.

[0103] Using the computational fluid dynamics method, the NS equation is used to numerically simulate the spatial flow field of the reference configuration, where the reference length c of the whole machine is 8.08m, and the reference area S is 16.57m 2 . Calculation status: Mach number Ma is 1.4, Reynolds number Re is 7.32×10 7 , the angle of attack α is 1 degree. The results show that the leading edge 1 of the lower surface of the aircraft and the trailing edge 2 of the lower surface of the aircraft are the main locations where compression waves and expansion waves are generated respectively, so that the positions of the compression region and the expansion region are determined;

[0104] Step 2, install the suction port in the compression area and the blowing port in the expansion area.

[0105] First...

Embodiment 2

[0119] Set four suction ports and four blow ports (configuration 2)

[0120] Step 1, determine the areas of compression and expansion of the lower surface of the aircraft.

[0121] Using the computational fluid dynamics method, the NS equation is used to numerically simulate the spatial flow field of the reference configuration, where the reference length c of the whole machine is 8.08m, and the reference area S is 16.57m 2 . Calculation status: Mach number Ma is 1.4, Reynolds number Re is 7.32×10 7 , the angle of attack α is 1 degree. The results show that the leading edge 1 of the lower surface of the aircraft and the trailing edge 2 of the lower surface of the aircraft are the main locations where compression waves and expansion waves are generated respectively, so that the positions of the compression region and the expansion region are determined;

[0122] Step 2, install the suction port in the compression area and the blowing port in the expansion area.

[0123] Fir...

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Abstract

The invention provides a method for suppressing sonic boom of a supersonic aircraft based on blowing air flow control. The location of the area; step 2, in the range of 5%-15% chordwise and 10%-80% spanwise in the compression area, arrange two to four suction ports; step 3, in the expansion area chordwise 80%-80% Between 95% and 10%-80% spanwise, two to four blowing ports are arranged. The advantages are as follows: the present invention can significantly reduce the intensity of the sonic boom observed on the ground by installing the air intake port in the compression area of ​​the lower surface of the aircraft wing and installing the air blow port in the expansion area, using the mutual interference between the shock wave and the expansion wave. . At the same time, it can increase the lift of the whole aircraft and reduce the drag, thereby improving the aerodynamic performance of the supersonic aircraft and better meeting the needs of supersonic flight.

Description

technical field [0001] The invention belongs to the technical field of sonic explosion suppression of supersonic aircraft, and in particular relates to a method for suppressing sonic explosion of supersonic aircraft based on blowing and suction flow control. Background technique [0002] With the acceleration of the world's globalization process and the improvement of living standards, air transport has become an indispensable mode of transportation for the development of politics, economy, culture and daily communication in today's world. After decades of research and development, the existing high subsonic aircraft technology has become relatively mature, and has reached a relatively high level in terms of safety, economy, comfort and environmental protection. Nevertheless, the flight time of high subsonic aircraft on long-distance transnational routes is still very long. In addition, the congestion level of the future air traffic system will bring serious problems to tra...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C21/02B64C30/00
CPCB64C21/025B64C30/00
Inventor 张力文韩忠华宋文萍
Owner NORTHWESTERN POLYTECHNICAL UNIV
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