Suscripción a Biblioteca: Guest
Página principal de la Biblioteca Digital de ICHMT Año actual Archivos Comité Ejecutivo Centro Internacional de Transferencia de Calor y Masa

Analysis of URANS capabilities on modeling airfoil pitching flows

DOI: 10.1615/ICHMT.2015.THMT-15.500
pages 279-282

A.F. Medina
School of Mechanical Engineering, Federal University of Uberlandia, Av. Joao Naves de Avila 2121, Campus Santa Monica, 38408100 Uberlandia, Minas Gerais, Brasil

F. J. Souza
School of Mechanical Engineering, Federal University of Uberlandia, Av. Joao Naves de Avila 2121, Campus Santa Monica, 38408100 Uberlandia, Minas Gerais, Brasil

Sinopsis

This document describes the investigation of the behavior of the flow over a pitching NACA0012 airfoil at Reynolds number Re=100,000 and Re=2,500,000 of the analysis of a two-dimensional k-ω SST (Shear Stress Transport) simulation. The behavior of the flow wake at the trailing edge is studied by the analysis of streamlines for each incidence angle and results are compared by the study of theoretical concepts and experimental data. The use of standard Unsteady Reynolds-Averaged Navier-Stokes (URANS) simulation has shown accuracy in predicting stall and reattachment incidence angles for upstroke and downstroke. The simulations were also capable of capturing flow information in agreement with experiments despite the over prediction of lift and drag coefficients, due to the two-dimensional simplification. The study has also compared the two-dimensional URANS k-ω SST model simulation data with previous results from three-dimensional simulation Large Eddy Simulation (LES) model analysis, showing that the qualitative behavior of the hysteresis loop is close for both computations, although there is a quantitative deviation in the results for upstroke and downstroke in the lift coefficient loop.

ICHMT Digital Library

Bow shocks on a jet-like solid body shape. Thermal Sciences 2004, 2004. Pulsed, supersonic fuel jets - their characteristics and potential for improved diesel engine injection. PULSED, SUPERSONIC FUEL JETS - THEIR CHARACTERISTICS AND POTENTIAL FOR IMPROVED DIESEL ENGINE INJECTION
View of engine compartment components (left). Plots of temperature distributions in centreplane, forward of engine (right). CHT-04 - Advances in Computational Heat Transfer III, 2004. Devel... DEVELOPMENT AND CURRENT STATUS OF INDUSTRIAL THERMOFLUIDS CFD ANALYSIS
Pratt & Whitney's F-135 Joint Strike Fighter Engine under test in Florida is a 3600F class jet engine. TURBINE-09, 2009. Turbine airfoil leading edge stagnation aerodynamics and heat transfe... TURBINE AIRFOIL LEADING EDGE STAGNATION AERODYNAMICS AND HEAT TRANSFER - A REVIEW
Refractive index reconstructed field. (a) Second iteration. (b) Fourth iteration. Radiative Transfer - VI, 2010. Theoretical development for refractive index reconstruction from a radiative ... THEORETICAL DEVELOPMENT FOR REFRACTIVE INDEX RECONSTRUCTION FROM A RADIATIVE TRANSFER EQUATION-BASED ALGORITHM
Two inclusion test, four collimated sources. Radiative Transfer - VI, 2010. New developments in frequency domain optical tomography. Part II. Application with a L-BFGS associated to an inexa... NEW DEVELOPMENTS IN FREQUENCY DOMAIN OPTICAL TOMOGRAPHY. PART II. APPLICATION WITH A L-BFGS ASSOCIATED TO AN INEXACT LINE SEARCH