Contributions to HiLiftPW-3 Using Structured, Overset Grid Methods

Abstract

The High-Lift Common Research Model (HL-CRM) and the JAXA Standard Model (JSM) were analyzed computationally using both the OVERFLOW and LAVA codes for the third AIAA High-Lift Prediction Workshop. Geometry descriptions and the test cases simulated are described. With the HL-CRM, the effects of surface smoothness during grid projection and the effect of partially sealing a flap gap were studied. Grid refinement studies were performed at two angles of attack using both codes. For the JSM, simulations were performed with and without the nacelle/pylon. Without the nacelle/pylon, evidence of multiple solutions was observed when a quadratic constitutive relation is used in the turbulence modeling; however, using time-accurate simulation seemed to alleviate this issue. With the nacelle/pylon, no evidence of multiple solutions was observed. Laminar-turbulent transition modeling was applied to both JSM configuration, and had an overall favorable impact on the lift predictions. Nomenclature AR = wing aspect ratio= total number of grid points Re = Reynolds number based on reference chord length S = reference wing area x = x-coordinate direction y = y-coordinate direction α = angle of attack η = non-dimensional spanwise coordinate, 2y/b Subscripts ∞ = free-stream conditions

A generalised implementation of eN transition method for airfoils and wind turbine blades

“…[3], [4], [5]) and the amplification factor transport models (AFT) by Coder (Ref. [6], [7]). All LCTM models employ the same concept, i.e.…”

Preliminary scale-resolving simulations of laminar-to-turbulent transition in swept-wing flow

“…The lack of reliability of current models to predict laminar-to-turbulent transition over the flight envelop of aircraft is still limiting the extent to which design can rely on computational tools, while making costly wind tunnel and flight tests a necessity [2]. Prediction of transition on practical three-dimensional wing geometries using the e N method coupled with laminar boundary layer and linear stability codes [3,4] or local statistical correlation CFD models such as the γ − Re θ Langtry-Menter model [5] have proven challenging [6][7][8], whereas transitional hybrid RANS-LES solvers have shown encouraging but still mitigated results [9][10][11]. The crossflow models implemented in RANS solvers [12,13,15,16] account for the effect of roughness in a somewhat rudimentary way.…”

Computational analysis of transitional and massively separated flows with application to wind turbines

“…The authors of the model utilize a formula which estimates the H factor using a local pressure gradient parameter H L . The version implemented in this work follows the formulation presented by Coder at al in [96]:…”