An aircraft with integrated flow control and aerodynamic matching design method

Abstract

The invention discloses an aircraft employing an integrated flow control technology. A discharge flow path is arranged on the wall surface of an inner passageway of an air intake duct, low-quality air flow is introduced into the interior of an engine bay, equipment in the engine bay is cooled while the performance of the air intake duct is improved, then air is exhausted through an ejector nozzle, and an effect of ejection thrust augmentation is further achieved. A flow restriction throat is arranged in the discharge flow path, to adjust the actual match working point. The invention also provides an aerodynamic matching design method of the aircraft. The discharge flow path performance curve and the ejector nozzle performance curve are obtained through the numerical simulation means or wind tunnel tests, the matching common working point is determined on the basis of the flow continuity principle and the condition of same engine bay pressure. According to the invention, the total pressure recovery coefficient and the outlet uniformity of the air intake duct can effectively enhanced, and obvious benefits in terms of reducing the aerodynamic resistance, improving the radar stealth performance of the aircraft and the like are also achieved.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to an integrated flow control technology applicable to a subsonic air inlet. Background technique [0002] As one of the important components of the air-breathing propulsion system, the air intake is responsible for many functions such as flow capture and regulation, incoming kinetic energy conversion and utilization, outlet flow velocity and uniformity adjustment, etc., and has a direct impact on the working efficiency of the entire propulsion system. Impact. In order to reduce aerodynamic drag, radar cross section (RCS), and improve the stealth performance of aircraft, more and more advanced subsonic aircraft adopt buried air inlets or S-curved air inlets without partitions. design plan. [0003] However, since the air intake of the buried air intake is completely integrated with the surface of the fuselage, it cannot be provided with a boundary layer partition in front of the inl...

AI Technical Summary

Problems solved by technology

Because they belong to different aircraft subsystems, the auxiliary air intake device is usually designed separately from the main air intake, and the air is bleed through the auxiliary air intake device which is specially designed and independently arranged in other parts of the airframe, which will cause a certain aerodynamic resistance. The radar stealth performance of the aircraft is also detrimental

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