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摘要:
冲压发动机喷管推力系数的准确测量十分重要。传统的测力天平受环境噪声等外界因素的影响较大，因此，考虑通过测量喷管出口截面的速度、压力和密度分布，直接根据定义获得推力系数。以典型过膨胀状态下单边膨胀喷管的复杂超声速内流场为研究对象，提出一套基于粒子图像测速(PIV)的多物理场和推力系数的非接触式重构测量方法。通过PIV虚拟实验，综合评估了所提方法的理论精度。结果表明：基于PIV测得的多物理场，利用定义式直接测得的喷管推力系数约为0.779，相比于参考值0.771，相对误差仅为1.04%，从而验证了所提方法的可行性和准确性。
Abstract:Accurate measurement of the thrust coefficient of ramjet nozzles is crucial. Traditional force balances are highly susceptible to external factors such as ambient noise and signal interference. Therefore, the paper proposed directly obtaining the thrust coefficient based on the definition by measuring the velocity, pressure, and density distributions at the nozzle outlet. A non-intrusive reconstruction measurement scheme based on particle image velocimetry (PIV) was proposed for multiple physical fields and the thrust coefficient of a typical single expansion ramp nozzle under over-expansion conditions. The theoretical accuracy of the reconstruction scheme was comprehensively evaluated using synthetic PIV experiments. The results indicate that the thrust coefficient of the nozzle, measured using the reconstructed multi-physical fields from PIV, is about 0.779, with a relative error of only 1.04% compared to the reference value of 0.771. This confirms the feasibility and accuracy of the proposed method.
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图 5 重构压力场与CFD参考压力场的对比
Figure 5. Comparison of reconstructed pressure field and CFD reference pressure field
图 7 虚拟PIV速度场的u/v分量及其对应的绝对误差
Figure 7. u/v components of synthetic PIV velocity field and corresponding absolute error distribution
图 8 重构压力场及其相对误差分布
Figure 8. Reconstructed pressure field and corresponding relative error distribution
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