Leading-edge bluntness effects on the hypersonic flow over the double wedge at multiple aft-wedge angles
نویسندگان
چکیده
The present numerical investigation focuses on the leading edge bluntness effects double-wedge with varied aft-wedge angles exposed to low enthalpy hypersonic free stream conditions. ratio in this study varies, ranging from R/L1 = 0 (sharp edge) 0.577 (maximum allowable bluntness), along angle varying between {\theta}2 450 and 600. Noticeably, even a small can completely change shock interaction pattern compared its sharp geometrical counterpart due detached shock, enlarged separation bubble, location of various shock-waves concerning it. Critical ratios exist for angle, but increasing makes flow field highly unsteady some ratios. Nevertheless, these such configurations are reported using mean bubble size. Moreover, work unravels cause unsteadiness flow-fields spatial-temporal evolution wall pressure distribution, Fast Fourier Transform (FFT) fluctuation signal at compression corner supports deduced observation help energy-based Proper Orthogonal Decomposition (POD). increased shock-boundary layer strength moves point upstream beyond junction cylindrical inclined fore-wedge surface, accompanying sudden direction motion that perturb shear set self-sustained, field.
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ژورنال
عنوان ژورنال: Physics of Fluids
سال: 2023
ISSN: ['1527-2435', '1089-7666', '1070-6631']
DOI: https://doi.org/10.1063/5.0149939