Date Available
4-26-2011
Year of Publication
2010
Degree Name
Master of Science in Mechanical Engineering (MSME)
Document Type
Thesis
College
Engineering
Department
Mechanical Engineering
First Advisor
Dr. Vincent R. Capece
Abstract
The steady flow aerodynamics of a cascade of compressor airfoils is computed using a two-dimensional thin layer Navier-Stokes flow solver. The Dhawan and Narasimha transition model and Mayle‟s transition length model were implemented in this flow solver so that transition from laminar to turbulent flow could be included in the computations. A method to speed up the convergence of the fully turbulent calculations has been introduced. In addition, the effect of turbulence production formulations and including streamline curvature correction in the Spalart-Allmaras turbulence model on the transition calculations is studied. These transitional calculations are correlated with the low and high incidence angle experimental data from the NASA-GRC Transonic Flutter Cascade. Including the transitional flow showed a trendwise improvement in the correlation of the computational predictions with the pressure distribution experimental data at the high incidence angle condition where a large separation bubble existed in the leading edge region of the suction surface.
Recommended Citation
Hariharan, Vivek, "TRANSITIONAL FLOW PREDICTION OF A COMPRESSOR AIRFOIL" (2010). University of Kentucky Master's Theses. 44.
https://uknowledge.uky.edu/gradschool_theses/44
