College of Engineering and Natural Sciences Mechanical Engineering Department 1 Project Number : PS 7.1 Rotorcraft Fuselage Drag Study using OVERFLOW-D2 on a Linux Cluster PI: Associate Professor EPN Duque tel : Northern Arizona University Graduate Assistant/Research Engineer: Nathan Scott 2004 RCOE Program Review May 4, 2004

College of Engineering and Natural Sciences Mechanical Engineering Department 2 Background/ Problem Statement: Evaluate fuselage force and moment prediction capability of the OVERFLOW2 and OVERFLOW-D Utilize cost effective computer systems

College of Engineering and Natural Sciences Mechanical Engineering Department 3 Technical Barriers or Physical Mechanisms to Solve : Appropriate grid generation over specific aircraft Lift and drag forces over simplified shapes such as prolate spheroid Grid sensitivity studies required Unsteady flow capturing on bluff bodies

College of Engineering and Natural Sciences Mechanical Engineering Department 4 Task Objectives: Using the OVERFLOW code Evaluate drag prediction on a prolate spheroid Evaluate drag prediction on a helicopter fuselage Evaluate and document effects of grid resolution Evaluate turbulence models upon predictions. 1-eqn, 2-eqn, DES Compare results with Penn State Methods

College of Engineering and Natural Sciences Mechanical Engineering Department 5 Approaches: OVERFLOW2 Code Grid Generation Near body grid refinement in boundary layer Grid adaptation in the field for vortical flow Turbulence models Baldwin-Barth Spalart-Almaras k-  Mentor-SST include Detached Eddy Simulation (DES)

College of Engineering and Natural Sciences Mechanical Engineering Department 6 Overview u Explain S-A and SST Detached Eddy simulation u Discuss DES Implementation in OVERFLOW u Circular Cylinder results u 6:1 Prolate Spheroid results

College of Engineering and Natural Sciences Mechanical Engineering Department 7 Experimental Data u Virginia Tech Stability Wind Tunnel –Wetzel, Simpson, Ahn u 1.37 m 6:1 Prolate Spheroid u Free stream conditions –α=20º, Re=4.2E 6, Ma=0.16 u Coefficient of Pressure (Cp), Skin Friction (C f )from Wetzel Dissertation u U/u*, y+ from Simpson’s Website

College of Engineering and Natural Sciences Mechanical Engineering Department 8 CFD Methodology u Reynolds Averaged Navier-Stokes Equations –OVERFLOW-D code developed at NASA and Army –Uses detailed overset grids –Allows for detailed geometry definition –Captures viscous effects such as unsteady flow separation u OVERFLOW2 used for turbulence model study and Implementation of DES –Scalar penta-diagonal scheme –1st order difference in time –2 nd or 4 th order RHS (OVERFLOW2) –2nd and 4th order central difference dissipation terms

College of Engineering and Natural Sciences Mechanical Engineering Department 9 Detached Eddy Simulation u First Formulated by Spalart as a modification to S-A model in u Later generalized to any model by Strelets in u First step was to modify the S-A model

College of Engineering and Natural Sciences Mechanical Engineering Department 10 S-A-DES formulation u Change distance to wall in S-A model d w to –Ĩ=min(d w,C DES ∆) –∆ is the maximum of the grid spacing in three dimensions- ∆=max(δ X, δ Y, δ Z ) –C DES =0.65

College of Engineering and Natural Sciences Mechanical Engineering Department 11 k-  -SST-DES Formulation u Change k-transport source term: ρβ*kω=ρk 3/2 /Ĩ –Ĩ=min(l k-ω,C DES ∆) –l k-ω =k 1/2 /(β*ω) –∆ is the maximum of the grid spacing in three dimensions- ∆=max(δ X, δ Y, δ Z ) –C DES =(1-F 1 ) C k-ε +F 1 C k-ω –C k-ε =0.61, C k-ω =0.78 At equilibrium reduces to an algebraic mixing-length Smagorinski type model.

College of Engineering and Natural Sciences Mechanical Engineering Department 12 Implementation in OVERFLOW u Determine grid cell edge lengths in J,K,L directions –One sided difference at boundaries –Central difference otherwise u Background Cartesian Grids - DES always enabled

College of Engineering and Natural Sciences Mechanical Engineering Department 13 Circular Cylinder Test Case u Re=140,000, Ma=0.2 u Fully Turbulent u S-A, S-A-DES, SST-DES turbulence models u 7.6 million grid points –Near body 181 by 60 by 99 –Background 426 by 61 by 252 –Off Body grid resolution 0.05 the diameter –H type block grid extends 10 diameters –2 total grids u Methods –4 th central difference in space –1 st order Beam-Warming in time u Inviscid wall Boundary Conditions

College of Engineering and Natural Sciences Mechanical Engineering Department 14 Other DES work with Cylinder u Travin, A, Shur, M, Strelets, M, Spalart, P –Re = 50,000 and 140,000 –Laminar Separation »Laminar Separation »LES in Background –Turbulent Separation »Run Fully Turbulent »Compares to higher Re

College of Engineering and Natural Sciences Mechanical Engineering Department 15 Iso-surface visualization comparison Circular Cylinder Travin-DES OVERFLOW S-A-DES OVERFLOW URANS (Not Unsteady Yet) OVERFLOW k-  -SST-DES

College of Engineering and Natural Sciences Mechanical Engineering Department 16 Unsteady Pressure coefficient for 1 drag cycle

College of Engineering and Natural Sciences Mechanical Engineering Department 17 Average Pressure coefficient for 1 drag cycle

College of Engineering and Natural Sciences Mechanical Engineering Department 18 Conclusions from Circular Cylinder u S-A DES in OVERFLOW looks promising –More fine scale resolution –Cross Flow on “2-D” cases –Comparable comparisons to Experimental Data  k-  -SST DES in OVERFLOW also looks promising –SST has been shown to approximate separation better so more desirable in shear layer –More verification needs to be done

College of Engineering and Natural Sciences Mechanical Engineering Department 19 6:1 Prolate Spheroid Test Case u Re=4,200,000, Ma=0.16 u Trip to Turbulence at x/L=0.2 u S-A, S-A-DES, SST-DES turbulence models u 7 million grid points –Near body 361 by 310 by 45 –First off body Grid spacing 0.08 the length –Remaining off body grids reduce in resolution by half –Off body grids extent to 10 times the length –61 Total grids –Grid shown to be convergent in Previous Study u Methods –4 th central difference in space –1 st order Beam-Warming in time

College of Engineering and Natural Sciences Mechanical Engineering Department 20 Other DES work with 6:1 Prolate Spheroid u Rhee, S. H. and Hino,T. –Re = 4,200,000 Ma=0,16 –Run Steady and Unsteady –Showed under prediction of Lift

College of Engineering and Natural Sciences Mechanical Engineering Department 21 Surface Skin Friction and vorticty contour comparison for 6:1 Spheroid S-A S-A DES SSTSST DES

College of Engineering and Natural Sciences Mechanical Engineering Department 22 Comparison Of Lift and Pitching Moment for 6:1 Spheroid u All of the models fall with error for Pitching Moment u All of the models under predict lift Lift Pitching Moment Experiment0.61± ±0.04 SA SST S-A-DES SST-DES Rhee & Hino

College of Engineering and Natural Sciences Mechanical Engineering Department 23 Axial Surface Pressure at x/L=0.77

College of Engineering and Natural Sciences Mechanical Engineering Department 24 Velocity Profile at x/L=0.77 and 150º from Windward side

College of Engineering and Natural Sciences Mechanical Engineering Department 25 Axial Skin Friction at x/L=0.77

College of Engineering and Natural Sciences Mechanical Engineering Department 26 Streamlines on Leeside

College of Engineering and Natural Sciences Mechanical Engineering Department 27 6:1 Spheroid Conclusions u DES shown to work with overset grids u DES did not improve integrated forces u Skin friction remained the same u Surface pressure showed slight improvement u Velocity profiles remained the same close to surface y+<10 u Velocity profiles improved farther away from surface y+>100

College of Engineering and Natural Sciences Mechanical Engineering Department 28 Accomplishments u Summer work with Roger Strawn and Mark Potsdam at Ames u Presented at AIAA 43 rd Aerospace Sciences Meetings.

College of Engineering and Natural Sciences Mechanical Engineering Department 29 Future Work u Grid Refinement Study on 6:1 Prolate spheroid and DES u New research engineer, explore new LES u Apply DES and LES to helicopter fuselage