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Supersonic aircraft sonic boom suppression method based on blowing and sucking air flow control

A technology of flow control and supersonic speed, which is applied to supersonic aircraft, aircraft parts, aircraft control, etc., can solve the problems that affect passenger ride experience and travel efficiency, and the adverse effects of aircraft aerodynamic performance, so as to increase the lift of the whole aircraft and reduce the Drag, the effect of improving aerodynamic performance

Active Publication Date: 2021-03-26
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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  • Supersonic aircraft sonic boom suppression method based on blowing and sucking air flow control
  • Supersonic aircraft sonic boom suppression method based on blowing and sucking air flow control
  • Supersonic aircraft sonic boom suppression method based on blowing and sucking air 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

[0120] Set four suction ports and four blow ports (configuration 2)

[0121] Step 1, determine the areas of compression and expansion of the lower surface of the aircraft.

[0122] 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;

[0123] Step 2, install the suction port in the compression area and the blowing port in the expansion area.

[0124] Fir...

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Abstract

The invention provides a supersonic aircraft sonic boom suppression method based on blowing and sucking air flow control. The method comprises the following steps: step 1, carrying out numerical simulation on a flow field of a supersonic aircraft to obtain positions of a compression area and an expansion area on the lower surface of an aircraft wing in a supersonic cruise state; 2, arranging two to four air suction ports within the range of 5%-15% of the chordwise direction and 10%-80% of the spanwise direction of the compression area; and 3, arranging two to four air blowing openings in the range of 80%-95% of the chordwise direction and 10%-80% of the spanwise direction of the expansion area. The method has the advantages that the air suction port is formed in the compression area of thelower surface of the aircraft wing, the air blowing port is formed in the expansion area, and the sonic boom intensity observed on the ground can be remarkably reduced through the mutual interferenceeffect between shock waves and expansion waves. Meanwhile, the lift force of the whole aircraft can be increased, and the resistance is reduced, so that the aerodynamic performance of the supersonicaircraft is improved, and the supersonic flight requirement is better met.

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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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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