Control of Massive Separation on A Thick-Airfoil Wing: A Computational and Experimental Study

The objective of this research is mutual validation of computational analysis and experimental measurements of baseline and controlled flow over a blunt configuration. A rectangular wing with a 36 percent thick airfoil was selected as a test case, representing a rotor pylon fairing. However, the results are relevant to thick airfoils in general, and contribute to the study of turbulent boundary layer separation and control. Despite the apparently simple geometry, previous measurements on this NACA 0036 airfoil proved challenging for computational analysis. Computational analysis, using DES, provided accurate prediction of the the massive separation and the effects of the oscillatory flow control. Both the aerodynamic coefficients variation with angle of attack, and the pressure distribution on the wing were in good agreement with measurements. These results stand in contrast to the previous failure of incompressible RANS solutions to reproduce the massive separation, its effect on aerodynamic coefficients, and the impact of flow control from t different slots.

[1]  Antony Jameson,et al.  Validation of a multigrid method for the Reynolds averaged equations , 1988 .

[2]  P. Spalart.  Comments on the feasibility of LES for wings, and on a hybrid RANS/LES approach , 1997 .

[3]  J. Gordon Leishman,et al.  Principles of Helicopter Aerodynamics , 2000 .

[4]  Israel J Wygnanski,et al.  Download reduction on a three dimensional V-22 model using active flow control , 2002 .

[5]  A. Jameson.  ANALYSIS AND DESIGN OF NUMERICAL SCHEMES FOR GAS DYNAMICS, 1: ARTIFICIAL DIFFUSION, UPWIND BIASING, LIMITERS AND THEIR EFFECT ON ACCURACY AND MULTIGRID CONVERGENCE , 1995 .

[6]  R. F. Warming,et al.  An implicit finite-difference algorithm for hyperbolic systems in conservation-law form. [application to Eulerian gasdynamic equations , 1976 .

[7]  S. Hoerner.  Fluid-Dynamic Lift , 1985 .

[8]  James Mabe,et al.  Boeing active flow control system for the V-22 , 2000 .

[9]  Z. Wang,et al.  A Modified Turbulence Model on Predicting Separated Airfoil Flow , 2002 .

[10]  Tung,et al.  Active Flow Control Measurements and CFD on a Transport Helicopter Fuselage , 2005 .

[11]  L. A. Young,et al.  Experimental investigation of advanced hub and pylon fairing configurations to reduce helicopter drag , 1993 .

[12]  M. S. Chandrasekhara,et al.  Active Separation Control Measurements and Computations for a NACA 0036 Airfoil , 2003 .

[13]  Luigi Martinelli,et al.  Large eddy simulation of compressible flow using a parallel, multigrid driven algorithm , 1996 .

[14]  Avi Seifert,et al.  Generic Transport Aft-body Drag Reduction using Active Flow Control , 2004 .

[15]  James R. Forsythe,et al.  Detached-Eddy Simulation around a Forebody at High Angle of Attack , 2003 .

[16]  Richard M. Carlson,et al.  Helicopter Performance—Transportation's Latest Chromosome: The 21st Annual Alexander A. Nikolsky Lecture , 2002 .

[17]  A. Jameson.  Time dependent calculations using multigrid, with applications to unsteady flows past airfoils and wings , 1991 .

[18]  K. Squires.  Detached-Eddy Simulation: Current Status and Perspectives , 2004 .

[19]  R Spalart Philippe,et al.  Young-Person''s Guide to Detached-Eddy Simulation Grids , 2001 .

[20]  A. Elmiligui,et al.  Numerical Study of Flow Past a Circular Cylinder Using RANS, Hybrid RANS/LES and PANS Formulations , 2004 .

[21]  P. Durbin.  SEPARATED FLOW COMPUTATIONS WITH THE K-E-V2 MODEL , 1995 .

[22]  D. C. McCormick,et al.  BOUNDARY LAYER SEPARATION CONTROL WITH DIRECTED SYNTHETIC JETS , 2000 .

[23]  Juan J. Alonso,et al.  Multigrid unsteady Navier-Stokes calculations with aeroelastic applications , 1995 .

[24]  P. Spalart.  A One-Equation Turbulence Model for Aerodynamic Flows , 1992 .

[25]  Eran Arad,et al.  Analysis of boundary layer separation over a bump using large eddy simulation , 2001 .

[26]  Ahmed Hassan,et al.  Transverse and near-tangent synthetic jets for aerodynamic flow control , 2000 .