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为了研究加速/减速过程中超声速进气道的起动/不起动现象,对二元超声速进气道的二维流场进行了定常/非定常数值模拟.分析了在来流马赫数为1.75~2.05范围内4种不同加速度绝对值对进气道气动性能的影响,并对定常/非定常模拟方法的结果进行了对比.结果表明:与定常模拟时相比,非定常数值模拟时进气道的流场特征在加速起动过程中和减速不起动过程中均存在明显的滞后现象,且加速度绝对值越大,滞后现象越明显;非定常模拟时的进气道处于起动状态时,其气动性能存在迟滞现象;当加速度绝对值一定时,进气道起动过程耗费的时间大于不起动过程耗费的时间.
In order to study the onset / non-starting of the supersonic inlet during acceleration / deceleration, the two-dimensional flow field of the binary supersonic inlet was simulated by steady / unsteady flow. The results show that when the Mach number is 1.75 ~ 2.05 The influence of four different acceleration absolute values on the aerodynamic performance of the inlet is compared and the results of the steady-state / unsteady simulation are compared.The results show that compared with the steady-state simulation, The characteristics of the flow field have obvious hysteresis during acceleration and deceleration, and the greater the absolute value of acceleration, the more obvious the hysteresis phenomenon. When the inlet is unsteady, the aerodynamic performance Hysteresis phenomenon; when the absolute value of acceleration is certain, the time taken to start the intake passage is longer than the time spent without starting the process.