By Chunhua Sheng
This publication offers a complete description of numerical tools and validation techniques for predicting transitional flows in accordance with the Langtry–Menter neighborhood correlation-based transition version, built-in with either one-equation Spalart–Allmaras (S–A) and two-equation Shear tension shipping (SST) turbulence versions. A comparative research is gifted to mix the respective advantages of the 2 coupling tools within the context of predicting the boundary-layer transition phenomenon from basic benchmark flows to practical helicopter rotors.
The e-book will of curiosity to business practitioners operating in aerodynamic layout and the research of fixed-wing or rotary wing airplane, whereas additionally providing complicated studying fabric for graduate scholars within the study parts of Computational Fluid Dynamics (CFD), turbulence modeling and comparable fields.
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Additional info for Advances in Transitional Flow Modeling: Applications to Helicopter Rotors
This modiﬁcation is essential for capturing the flow physics in rotatory wings and obtaining accurate predictions of aerodynamic performance for the entire operating envelope (Sheng et al. 2016). 1 31 Local Free-Stream Turbulence Intensity From Eq. 16), the transition onset Reynolds number is determined based on both turbulence intensity and pressure gradient. A decrease in turbulence intensity would increase the transition onset Reynolds number, and thus move the transition onset location downstream.
Combined with empirical correlations for the transition onset Reynolds number, this method can be easily incorporated into general structured and unstructured grid CFD codes. The vorticity Reynolds number (or alternatively the strain rate Reynolds number) is deﬁned as: qy2 @u qy2 ¼ Rev ¼ S l @y l ð3:1Þ where q is density, l is dynamic viscosity, u is the local velocity, y is the distance to the nearest wall and S is the shear strain rate. Examining the Blasius boundary layer velocity proﬁle, Driest and Blumer (1963) concluded that there is a limiting value of the vorticity Reynolds number in an undisturbed Blasius boundary layer, and the © The Author(s) 2017 C.
ASME J Turbomach 120:613–620 Walters DK, Leylek JH (2002) A new model for boundary-layer transition using a single-point RANS approach. In: ASME IMECE’02, IMECE2002-HT-32740 Walters DK, Leylek JH (2004) A new model for boundary-layer transition using a single-point RANS approach. J Turbomach 126(1):193–202. 1622709 Wang J, Sheng C (2014) Validations of a local correlation-based transition model using an unstructured grid CFD solver. AIAA-2014-2211. Paper presented at 7th AIAA Theoretical Fluid Mechanics Conference, Atlanta, Georgia, 16–20 June 2014 Wang J, Sheng C (2015) A comparison of a local correlation-based transition model coupled with SA and SST turbulence models.