A fast method for determining the parameters after the intersection of two oblique shock waves on the same side
A determination method and shock wave intersection technology, which is applied in the testing of machines/structural components, measuring devices, instruments, etc., can solve the problems of large result error and cumbersome iterative process, and achieve the effect of simple method and high precision
Inactive Publication Date: 2018-04-06
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Repeated iterations on the flow direction according to these two conditions can calculate the parameters of the intersecting gas flow, such as pressure, flow direction and Mach number (refer to "Gas dynamics" (Zucrow M J, Hoffman J D)), but the iterative process is relatively cumbersome
There are also literatures that directly take the total turning angle of the airflow after the intersection as the sum of the turning angles of the first two shock waves (such as "The dynamics and thermodynamics of compressible fluid flow" (Shapiro A H)), when the turning angle is large, the result error will be larger
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[0017] The present invention will be further described below in conjunction with the accompanying drawings.
[0018] A method for quickly determining the parameters after the intersection of two oblique shock waves on the same side. The sum of the turning angle of the first shock wave and the turning angle of the second shock wave is used as the total turning angle, and the calculation is based on the total turning angle The airflow parameter after the new shock wave generated after the intersection of the first shock wave and the second shock wave, and then calculate the difference between the airflow parameter and the airflow parameter after the second shock wave, and determine the first shock wave according to the obtained difference The turning angle caused by the reflected wave generated after intersecting with the second shock wave, so as to determine the downstream parameters after the intersection of the first shock wave and the second shock wave.
[0019] The method s...
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The invention discloses a rapid determination method for parameters after intersection of two ipsilateral oblique shock waves so as to generate the sum of a turning angle of first shock wave and a turning angle of second shock wave to act as a total turning angle. Flow parameters after generation of new shock wave after intersection of the first shock wave and the second shock wave are calculated according to the total turning angle. Then the difference of the flow parameters of the flow parameters of the second shock wave is calculated. A turning angle generated by reflection wave generated after intersection of the first shock wave and the second shock wave is determined according to the obtained difference so that downstream parameters after intersection of the first shock wave and the second shock wave are determined. According to the rapid determination method for the parameters after intersection of the two ipsilateral oblique shock waves, the parameters after intersection of the two shock waves can be conveniently determined without iterative solution so that the method is simple and high in precision.
Description
technical field [0001] The invention relates to a method for quickly determining parameters after two oblique shock waves on the same side intersect, which belongs to fluid mechanics technology. Background technique [0002] The intersection of two oblique shock waves on the same side is a common phenomenon in supersonic flow. After the intersection, a new shock wave will be formed, and slip flow discontinuity and reflection waves will be generated. The airflow on both sides of the slip flow discontinuity satisfies the conditions of equal pressure and the same flow direction. . According to these two conditions, the flow direction can be iteratively calculated to obtain parameters such as the pressure, flow direction, and Mach number of the intersecting airflow (refer to "Gas dynamics" (Zucrow M J, Hoffman J D)), but the iterative process is relatively cumbersome. There are also literatures that directly take the total turning angle of the airflow after the intersection as ...
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IPC IPC(8): G01M9/00
CPCG01M9/00
Inventor 王磊张堃元金志光苏纬仪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS