Wall modeled large-eddy simulations of flow over the Sandia transonic hump
View Video Presentation: https://doi. org/10.2514/6.2023-3972. vid Wall-modeled large-eddy
simulations (WMLES) are conducted for the flow over the Sandia Axisymmetric Transonic …
simulations (WMLES) are conducted for the flow over the Sandia Axisymmetric Transonic …
Assessment of the shear stress transport dynamic ℓ 2− ω delayed detached eddy simulation in Bachalo–Johnson flow with shock-induced separation
Driven by the need for simulating compressible flows, Germano identity-based [Z. Yin and
PA Durbin,“An adaptive DES model that allows wall-resolved eddy simulation,” Int. J. Heat …
PA Durbin,“An adaptive DES model that allows wall-resolved eddy simulation,” Int. J. Heat …
[PDF][PDF] Wall-modeled large-eddy simulation of the Sandia Axisymmetric Transonic Bump
The prediction of complex flow phenomena such as three-dimensional juncture flows (Lee &
Pulliam 2019), smooth-body separation (Rumsey et al. 2019), and transonic shock-induced …
Pulliam 2019), smooth-body separation (Rumsey et al. 2019), and transonic shock-induced …
[HTML][HTML] Numerical Methods Comparison of Shock-Induced Separation on Transonic Axisymmetric Hump
M Zhang, Z Tian, S Tang, Z Wei, J Li - Applied Sciences, 2024 - mdpi.com
A transonic hump with a Mach number (M∞) of 0.875 was utilized to compare the prediction
capabilities of RANS, URANS, IDDES, and IDDES-SLA for shock-induced separation. The …
capabilities of RANS, URANS, IDDES, and IDDES-SLA for shock-induced separation. The …
Wall modeled large-eddy simulations of flow over the Sandia Axisymmetric Transonic Bump
Wall-modeled large-eddy simulations (WMLES) are conducted for the flow over the Sandia
Axisymmetric Transonic Bump (ATB) at bump chord Reynolds number, Re= 1x10^ 6 and …
Axisymmetric Transonic Bump (ATB) at bump chord Reynolds number, Re= 1x10^ 6 and …
From high-fidelity high-order to reduced-order modeling for unsteady shock wave/boundary layer interactions
N Goffart - 2024 - iris.uniroma1.it
In transonic turbomachinery flows, the shock wave/boundary layer interaction is the primary
aerodynamic performance-limiting factor. For the next-generation engines, improvements in …
aerodynamic performance-limiting factor. For the next-generation engines, improvements in …