Abstract
Abstract
Highlights
It is of practical importance to investigate hypersonic compression-ramp flows with leading-edge bluntness
The direct numerical simulations (DNS) and Global stability analysis (GSA) were performed to study the effects of leading-edge bluntness on flow separation, the intrinsic instability and surface heat transfer
When the leading-edge radius is increased from zero to the critical value (0.5 mm), the compression-ramp flow becomes more unstable, with the unstable modes being characterised by higher growth rates
Summary
A compression ramp configuration (i.e. a flat plate followed by a ramp) is representative of many components for high-speed vehicles, such as air inlets, junctions, control surfaces, etc. Holden (1971) related the reversal trend to the bluntness–viscous interaction theoretically described by Cheng et al (1961) According to their studies, the boundary-layer displacement effects are dominant prior to the reversal point, while the leading-edge bluntness effects dominate the region where the size of the separated flow drops. The present study considers the hypersonic compression-ramp flows experimentally investigated by Roghelia et al (2017a,b), where streamwise heat-flux streaks were observed on the ramp surface for small leading-edge radii. Based on the aforementioned information, it is conjectured that the presence and absence of the heat-flux streaks are connected to the intrinsic instability which varies with the leading-edge radius To verify this hypothesis, we employ GSA and DNS to investigate the hypersonic compression-ramp flows in Roghelia et al (2017a).
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