Searched for: +
(1 - 5 of 5)
document
Hu, W. (author), Hickel, S. (author), van Oudheusden, B.W. (author)
The flow over a forward-facing〉 step (FFS) at Ma<sub>∞</sub> = 1.7 and Re<sub>δ0</sub> = 1.3718 × 10<sup>4</sup> is investigated by well-resolved large-eddy simulation. To investigate effects of upstream flow structures and turbulence on the low-frequency dynamics of the shock wave/boundary layer interaction (SWBLI), two cases are considered:...
journal article 2022
document
Hu, W. (author), Hickel, S. (author), van Oudheusden, B.W. (author)
The low-frequency unsteady motions behind a backward-facing step (BFS) in a turbulent flow at and are investigated using a well-resolved large-eddy simulation. The instantaneous flow field illustrates the unsteady phenomena of the shock wave/boundary layer interaction (SWBLI) system, including vortex shedding in the shear layer, the flapping...
journal article 2021
document
Laguarda, L. (author), Hickel, S. (author), Schrijer, F.F.J. (author), van Oudheusden, B.W. (author)
The response of asymmetric and planar shock interactions to a continuous excitation of the lower incident shock is investigated numerically. Incident shock waves and centred expansion fans are generated by two wedges asymmetrically deflecting the inviscid free stream flow at Mach 3. The excitations mechanisms considered are (i)Â pitching of...
journal article 2020
document
Xue, S. (author), Schrijer, F.F.J. (author), van Oudheusden, B.W. (author), Wang, Chengpeng (author), Shi, Zhiwei (author), Cheng, Keming (author)
In this paper the configurations of shock wave-boundary layer interactions (SWBLI) are studied theoretically and experimentally in Mach number 2 and 2.5 flows on test models with various wedge angles ranging from to. The proposed theoretical method couples the free interaction theory (FIT) with the minimum entropy production (MEP) principle...
journal article 2020
document
Giepman, R.H.M. (author), Schrijer, F.F.J. (author), van Oudheusden, B.W. (author)
High-resolution particle image velocimetry measurements were performed on laminar and transitional oblique shock wave reflections for a range of Mach numbers (M D 1:6-2:3), Reynolds numbers (Re<sub>xsh</sub> D 1.4×10<sup>6</sup>-3.5×10<sup>6</sup>) and flow deflection angles (θ 1°-5° or p3=p1 D 1.11-1.64). The laminar interactions revealed a...
journal article 2018
Searched for: +
(1 - 5 of 5)