Structure of crossing-shock-wave/turbulent-boundary-layer interactions

Advances in CFD prediction of shock wave turbulent boundary layer interactions

“…As it is seen from the perspective view and cross section III, the entire incident λ-shock structure reflects from the center plane in an irregular manner and remains intact, though somewhat distorted, propagating away from the center toward the fin surface. The additional cross sections that characterize details of the complex shock crossings between the cross sections I and III are considered in [173,177,178]. As shown in cross section III, two additional shock segments and two triple points are observed to form a result of this crossing.…”

“…Since that time, interest in this problem has greatly increased due to its relationship to scramjet propulsion since the crossing shock interaction constitutes a geometrical simplification of a hypersonic sidewall compression inlet. Symmetric interactions (i.e., α 1 = α 2 ) have been studied by [6,159,164,168,169,170,171,172,173,174,175,176,177,178,179,180,181,182,183,184,185,186,187,188,189,190,191,192,193,194,195,196,197,198,199,200,201,202,203,204,205,206,207,208,209]. Asymmetrical interactions (i.e., α 1 = α 2 ) have been studied by [6,164,167,…”

“…The most complete cycle of experimental research of the symmetrical interaction between crossing shock waves with a turbulent boundary layer for M ∞ = 3 and 4 is presented in [172,174,177,178,184,185,186]. In addition to the patterns of the limiting streamlines Studies dealing with unsteady effects are infrequent, but nonetheless extremely important.…”

“…The calculations conducted for symmetrical [159,164,170,174,175,176,177,180,181,182,183,184,186,188,189,190,191,192,193,199,200,201,202,203,204,205,206,208,209,210,213,214] and asymmetrical [164,187,192,193,197,199,202,203,204,208,209,211,212,213,214,215,216,218] interactions and for symmetrical fins mounted on the compression surface [190,219]. As it follows from review of investigations of the flow for symmetrical and asymmetrical intera...…”

Numerical simulation on supersonic shock wave/turbulent boundary interaction

“…A fin type structure was selected as test case for supersonic condition, sidewall compression angle is 11º×11º and narrowest width is 4.65cm, the expansion angle is 30º afterwards. Other simulating parameters could be found in literature [9] . For symmetrical characteristics of the configuration, half-module was adopted in the follow analysis and simulation.…”