Design method for inner channel molded surface of rectangular hypersonic speed air inlet channel
A design method, hypersonic technology, applied in turbine/propulsion inlet, combustion air/combustion-air handling, engine components, etc., which can solve problems such as non-starting, flight test failure, etc.
Active Publication Date: 2017-09-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology
For example, during the flight test of the X-51A hypersonic test aircraft in the United States, there were two problems with the inlet not starting, which led to the failure of the flight test.
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[0032] The invention discloses a method for designing an inner channel profile of a rectangular hypersonic air inlet. see Figure 1 to Figure 5 , which includes the following specific design steps:
[0033] 1. Based on the three-dimensional profile of the outer compression surface 1 of the hypersonic inlet and the flow field parameters of the inlet 2 of the inner channel.
[0034] 2. Determine the shrinkage ratio in the air inlet. Internal contraction ratio Ar t is defined as the ratio of the area of the section of the entrance 2 of the inner channel (that is, the section where the front edge of the lip mask is located) to the section of the throat 3. Internal contraction ratio Ar t The determination of the operation is carried out according to the method of starting ability factor S. The starting ability factor S is defined as:
[0035] S=(Ar t -AR t,等熵极限 ) / (AR t,Kantrowitz极限 -AR t,等熵极限 );
[0036] in
[0037] where M 0 is the flight Mach number, γ=1.4;
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The invention discloses a design method for the inner channel molded surface of a rectangular hypersonic speed air inlet channel. By the whole design procedures such as determining the inner contraction ratio of the air inlet channel, selecting a lip cover wave-matching form of an inner contraction section of the air inlet channel, designing a lip cover wave-shocking system of the inner contraction section of the air inlet channel, designing a control measure of a lip cover wave-shocking / boundary layer interference phenomenon, designing side plates of the two sides of the air inlet channel lip cover, and analyzing and adjusting and designing three-dimensional simulation of the inner channel molded surface of the air inlet channel, and introducing the start capacity factor S, the control measure of the wave-shocking / boundary layer interference, the control characteristic and the like, determiningthe inner contraction ratio of the air inlet channel and designing the inner channel lip cover compression surface, theshoulder molded surface and the lip cover side plates are completed, and meanwhile, the throat channel mach number requirement, the automatic start capacity requirement, the flow texture requirement and the like are met. The design method further provides a specific adjustment method for the design result of the inner channel molded surface of the air inlet channel according to the three-dimensional simulation result.
Description
technical field [0001] The invention relates to the field of aircraft design, in particular to a design method for a hypersonic air inlet. Background technique [0002] The hypersonic inlet is one of the three key components of the scramjet engine. It is responsible for capturing the incoming flow, compressing the incoming flow, and providing the required flow and quality airflow to the combustion chamber. The propulsion efficiency and stable working envelope of the fuel ramjet have an important influence. [0003] According to the geometric form of the hypersonic inlet, it can generally be divided into rectangular inlet, axisymmetric inlet, side pressure inlet, three-dimensional internal rotation inlet and other types. Among them, because of its relatively simple flow structure and geometric structure, and the convenience of integrated design with the aircraft precursor, the rectangular inlet is currently the mainstream solution that various hypersonic test vehicles in the...
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Login to View More IPC IPC(8): F02C7/04
CPCF02C7/04
Inventor 谭慧俊黄河峡谢文忠满延进张可心李鑫
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS