Laminar-turbulent transition may have considerable influence on the performance of moderate and high-speed aerodynamic vehicles. The two recently developed transition-sensitive models, SST-TR and kT-kL-ω, are employed to assess their abilities in resolving the complex underlying flow physics associated with flow structures over delta wings. In particular, their capabilities in capturing the aerodynamic characteristics of three-dimensional flow associated with vortex breakdown, shear-layer instabilities, and boundary-layer transition are assessed. These closures are employed to simulate vortex breakdown and near-wall flow structures over a delta wing planform with a moderate sweep angle of 50 deg at a Reynolds number of Re=6.2×105, where a combination of laminar, transitional, and turbulent flowfields coexist. Accuracy of these models in predicting boundary-layer transition adjacent to a delta wing surface with a high-sweep angle of 70 deg and Reynolds numbers of Re=1×106 and Re=1.2×106 is investigated. Large-eddy simulation with dynamic Smagorinsky subgrid scale model is also employed to assess its capability in predicting transition on delta wing planforms. All numerical simulations are compared with available experimental data found in the literature.
Performance of Transition-Sensitive Models in Predicting Flow Structures over Delta Wings
Journal of aircraft ; 52 , 1
2015
Article (Journal)
English
Incompressible flow over delta wings
AIAA | 1977
|Flow structure over delta wings
AIAA | 1995
|Vortex flow over delta and double-delta wings
AIAA | 1983
|Nonlinear Supersonic Potential Flow over Delta Wings
AIAA | 1981
|