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考虑进气道出口流场的影响,设计了针对非对称超声速来流矩形隔离段流场研究的直联式试验风洞,模拟进气道出口流场的各种非对称进口条件进行了吹风试验,并测量了隔离段壁面静压和隔离段进口皮托压力。研究发现,随隔离段进口流动非对称程度的增加,激波串长度增加而隔离段耐受反压的能力下降。考虑了隔离段进口流动非对称的影响,对Billig-Waltrup的激波串长度公式作了改进,故提高了激波串长度预测的精确程度。
Considering the influence of inlet flow field, a direct experimental wind tunnel designed for asymmetric supersonic flow in rectangular flow field was designed, and various asymmetric inlet conditions were simulated to conduct blow test , And measured the hydrostatic pressure at the isolation section and the inlet Pitot pressure at the isolation section. It is found that as the flow asymmetry increases in the inlet of the isolation section, the shockwave length increases and the isolation section withstands the pressure drop. Considering the asymmetric influence of the inlet flow in the isolation section, the formula of the shock length of Billig-Waltrup is improved, which improves the accuracy of shock train length prediction.