Numerical results are presented for the shock-boundary layer interactions in a hypersonic flow over a sharp leading edge compression corner. In this study, a second- order Godunov type scheme based on solving a Generalized Riemann Problem (GRP) at each cell interface is used to solve thin shear layer approximation of laminar Navier-Stokes (N-S) equations. The calculated flow-field shows general...

Hypersonic flow over a two-dimensional compression corner with Mach number of 7.7 and unit Reynolds 4.2 × 10 6 m ?1 is numerically investigated. Special emphasis given to the onset global instability respect three-dimensional perturbations. Global stability analysis performed for various ramp angles wall temperatures. It found that shock-induced separated system becomes unstable when angle beyo...

Hypersonic flow over a two-dimensional compression corner is investigated using computational fluid dynamics and global resolvent analysis in this study, which continuation of the work done by Hao et al. ( J . Fluid Mech. , vol. 919, 2021, p. A4). The same baseline free-stream conditions with Mach number 7.7 unit Reynolds 4.2 × 10 6 m −1 are considered. ramp angles range from 0° (equivalent to ...

A novel numerical scheme has been developed to simulate high speed viscous flows in complex geometries using unstructured grids. A characteristic–filter based shock capturing scheme is applied as a corrector step to a non–dissipative predictor scheme. This algorithm is being used to study shock turbulent boundary layer interactions and this paper presents the results of a turbulent flow at Mach...

A flap can be used as a high-lift device, in which a downward deflection results in a gain in lift at a given geometric angle of attack. To characterize the aerodynamic performance of a deflected surface in compressible flows, the present study examines a naturally developed turbulent boundary layer past the convex and concave corners. This investigation involves the analysis of mean and fluctu...

objective(s):the aim of this study was to improve flowability and compressibility characteristics of starch to use as a suitable excipient in direct compression tabletting. quasi-emulsion solvent diffusion was used as a crystal modification method. materials and methods: corn starch was dissolved in hydrochloric acid at 80˚c and then ethanol as a non-solvent was added with lowering temperature ...

This study used pressure-sensitive paint (PSP) and determined the surface pressure distributions for a compressible swept convex-corner flow. The freestream Mach numbers were 0.64 0.83. angle were, respectively, 10–17° 5–15°. Expansion compression near corner apex clearly visualized. For test case of shock-induced boundary layer separation, there greater spanwise gradient curved shocks. acquire...

A convex corner models the upper surface of a deflected flap and shock-induced boundary layer separation occurs at transonic speeds. This study uses micro-vortex generators (MVGs) for flow control. An array MVGs (counter-rotating vane type, ramp type co-rotating type) with height 20% thickness incoming is installed upstream corner. The pressure distributions are similar regardless presence MVGs...

Super- and hypersonic flow around aircraft elements is accompanied by the formation of a complex structure, which characterized presence strong shock waves, rarefaction contact discontinuities, separation reattachment flow. For such problems, interaction waves with viscous boundary layers characteristic. Such quite largely determines effectiveness aircraft. When flowing structures their power p...