Air inlet wave system configuration method for independent convergence of shock waves and isentropic compression waves

A technology of isentropic compression and configuration method, which is applied to the combustion of the intake port of the power plant, ground equipment, aircraft parts, etc., to achieve the effect of improving work efficiency and improving the recovery coefficient of total pressure

Active Publication Date: 2021-06-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, for the conventional design method based on multi-channel shock wave / isoentropic compression wave converging lip, the total pressure recovery coefficient and external resistance are two contradictory issues, and it is impossible to achieve both high total pressure recovery coefficient and low progress. Airway external resistance, must develop a new type of inlet design method

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  • Air inlet wave system configuration method for independent convergence of shock waves and isentropic compression waves
  • Air inlet wave system configuration method for independent convergence of shock waves and isentropic compression waves
  • Air inlet wave system configuration method for independent convergence of shock waves and isentropic compression waves

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[0023] The invention discloses a design method of a reverse compression large internal contraction ratio intake port compression system. see figure 1 , figure 2 , image 3 , Figure 4 As shown, the detailed implementation steps of the intake port with a design Mach number of 7 designed by the method of the present invention are described below.

[0024] (1). According to the design requirements of the hypersonic vehicle inlet, the design Mach number is 7, and the compression method adopts three-stage compression, and the compression angle of each stage is 4°, 4°, and 13°;

[0025] (2). If figure 1 As shown, according to the incoming flow Mach number M under design conditions ∞ =7 and the first stage compression angle δ 0 '=4°, according to the oblique shock wave theory, the Mach number M of the airflow after the first oblique shock wave is obtained 0 =6.281, the shock angle is β 0 '=11.02°, then by M 0 =6.281 and δ 2 '= 4 ° After the second shock wave, the Mach numb...

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Abstract

The invention provides an air inlet wave system configuration method for independent convergence of shock waves and isentropic compression waves. According to the method, shock waves of a compression surface of an air inlet are all converged at a lip position, and a virtual convergent point of isentropic compression waves behind the shock waves is arranged at the right upper part of the lip of the air inlet, so that the isentropic compression waves and other shock waves of the compression surface of the air inlet are independently converged, and the isentropic compression waves and lip cover shock waves generated by the lip cover of the air inlet form heterogeneous shock wave-isentropic compression wave interference. Compared with a conventional wave distribution mode that all shock waves and isentropic compression waves are converged at the lip position, the method has the advantages that the total pressure recovery coefficient of the throat of the air inlet can be greatly improved, the strength of the shock waves of the lip cover of the air inlet is weakened, the scale of a separation area formed by interference of the shock waves / boundary layers of the lip cover is reduced, and the low Mach number flow coefficient of the air inlet is improved. Especially for an air inlet with strong lip cover shock waves, the technical advantages of the invention are more obvious.

Description

technical field [0001] The invention relates to the field of hypersonic aircraft, in particular to an inlet wave system configuration method suitable for independent convergence of shock waves with strong lip shock waves and isentropic compression waves. Background technique [0002] As an essential part of the air-breathing powered aircraft, the air intake duct plays a vital role in the stable operation of the power system. According to relevant studies, the total pressure recovery coefficient of the intake port is reduced by 1%, and the thrust loss of the power system is 1.2% to 1.5%. The factors that lead to the performance degradation of the intake port are complex and changeable, including design methods and actual working conditions. In the design stage, it is necessary to fully consider key design factors such as the configuration of the wave system of the inlet and the organization of the complex flow field in the inner channel. Among them, the total pressure loss ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02B64F5/00
CPCB64D33/02B64F5/00
Inventor 黄河峡唐学斌李灿民秦源谭慧俊李超张航
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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