RANS Simulation and Experiments on the Stall Behaviour of a Tailplane Airfoil

Wokoeck, Ralf; Grote, Arne; Krimmelbein, Normann; Ortmanns, Jens; Radespiel, Rolf; Krumbein, Andreas

doi:10.1007/978-3-540-33287-9_26

Cited by 4 publications

(3 citation statements)

References 11 publications

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“…The separated wake shows strong unsteadiness, a broadband frequency spectrum and large scale turbulent structures. There are many numerical and experimental investigations on flow separation from wings and airfoils and its impact on the aerodynamic characteristics 6,7,8,11,17,23,32,33,34 . But apart from research on tip vortex roll-up there are only few studies on the development of the separated wake spectrum downstream of the trailing edge.…”

Section: Introductionmentioning

confidence: 99%

Going for Experimental and Numerical Unsteady Wake Analyses Combined with Wall Interference Assessment by Using the NASA CRM-model in ETW

Lutz

Gansel²,

Godard³

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Detailed experimental and accompanying numerical studies on the development of unsteady wakes past an aircraft under stall conditions are currently prepared by a consortium of research institutions and universities. The experiments will be performed in the ETW cryogenic wind tunnel on the NASA Common Research Model. Besides wake surveys using time-resolved cryo PIV measuring technique, wall interference measurements are planned. The tests scheduled for July 2013 are funded by the European Commission in the 7 th framework program. In this paper results of preparatory CFD studies and wake analyses of the CRM model, the TR-PIV measuring technique and the ETW facility are presented along with the wind tunnel model and the planned test program. Nomenclature CFD = Computational Fluid Dynamics CRM = Comon Research Model b = wing span c = reference chord c l = lift coefficient c p = pressure coefficient DES = Detached Eddy Simulation 2 DPW = Drag Prediction Workshop ESP = Electronically Scanned Pressure ESWI RP = European Strategic Wind Tunnels Improved Research Potential ETW = European Transonic Windtunnel f = frequency HTP = horizontal tail plane k = turbulence kinetic energy L = turbulence length scale L 11 = longitudinal integral length scale LES = Large Eddy Simulation LU-SGS = lower-upper symmetric Gauss-Seidel M ∞ = freestream Mach number NTF = National Transonic Facility (U)RANS = (unsteady) Reynolds-Averaged Navier-Stokes Re = Reynolds number based on the reference chord length RMS = Root Mean Square S = wing reference area St = Strouhal number T t = total temperature TR-PIV = Time-Resolved Particle Image Velocimetry U = velocity U ∞ = freestream velocity x,y,z = Cartesian coordinates y + = wall distance normalized by the viscous length scale α = angle of attack ε = dissipation rate of turbulent kinetic energy η = spanwise position normalized by the wing half span

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Section: Introductionmentioning

confidence: 99%

Going for Experimental and Numerical Unsteady Wake Analyses Combined with Wall Interference Assessment by Using the NASA CRM-model in ETW

Lutz

Gansel²,

Godard³

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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show abstract

“…1,2,3,4 The separated wake at low Mach number and high angle of attack is characterized by occurrence of large turbulent structures and a broadband spectrum both, for airfoils and three-dimensional wing configurations. There are many investigations on flow separation from airfoils and wings 5,6,7,8,9,10,11,12,13 and dedicated experiments are available to verify numerical methods with regard to prediction of pressure distribution, boundary layer development and separation. But there are only few studies on the development of the separated wake and its spectrum downstream of the trailing edge.…”

Section: Introductionmentioning

confidence: 99%

Time-resolved Prediction and Measurement of the Wake past the CRM at high Reynolds number stall conditions

Lutz

2015

53rd AIAA Aerospace Sciences Meeting

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The development of the unsteady wake of transport aircraft under stall conditions and its impact on the empennage is challenging to predict and the flow physics is far from being understood. In the European ESWI RP project time-resolved PIV (TR-PIV) measurements on the separated wake of the NASA Common Research Model (CRM) were performed in the cryogenic European Transonic Windtunnel (ETW) for flight Reynolds number conditions supplemented by aerodynamic measurements for a great variety of inflow conditions. In the TR-PIV measurements both, low-speed stall (M∞ = 0.25, Re = 11.6 / 16.5M) and high-speed stall (M∞ = 0.85, Re = 19.8 / 30M) were considered and the frequency resolution was as high as 1 kHz enabling a sufficient characterization of the turbulent wake spectrum. Further hybrid RANS/LES simulations were performed for selected low-and high-speed stall conditions. In the present paper the numerical results are discussed and compared to the experiments and first evaluations of the PIV data are presented.

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“…To improve the accuracy of the stability analysis, the database methods are replaced by the linear stability code COAST3 7 . Especially for prediction of transition over 2D laminar separation bubbles an advancement was already achieved with this new code version 8 . The previous transition module could only be run in sequential mode and had to be converted, with regard to decent turn around times, to a parallel version.…”

Section: Introductionmentioning

confidence: 99%

Numerical Aspects of Transition Prediction for Three-Dimensional Configurations

Krimmelbein

Radespiel

Nebel³

2005

35th AIAA Fluid Dynamics Conference and Exhibit

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The feasibility to predict transition for three dimensional configurations is presented by means of a coupled program system consisting of a 3D Navier-Stokes solver, a transition module and a stability code. The assumption to use inviscid streamlines as integration paths for the N-factor calculation makes it possible to use linear stability theory in a straightforward way for three dimensional flows. The developed transition module has been adapted to be used with sequential and parallel computations to account for the increased computational demand for three dimensional configurations. Detailed investigations have been carried out, to show the ability of the Navier-Stokes code to provide data of three dimensional boundary layers of high accuracy needed for the stability analyses. Applications of the transition prediction method using the 2N-factor method for the case of an inclined prolate spheroid shows reasonably good results compared to experiments. First application of the transition prediction tool on a generic transport aircraft show promising results for the ability to predict transition on complex geometries.

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RANS Simulation and Experiments on the Stall Behaviour of a Tailplane Airfoil

Cited by 4 publications

References 11 publications

Going for Experimental and Numerical Unsteady Wake Analyses Combined with Wall Interference Assessment by Using the NASA CRM-model in ETW

Going for Experimental and Numerical Unsteady Wake Analyses Combined with Wall Interference Assessment by Using the NASA CRM-model in ETW

Time-resolved Prediction and Measurement of the Wake past the CRM at high Reynolds number stall conditions

Numerical Aspects of Transition Prediction for Three-Dimensional Configurations

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