Numerical Simulation of DLR-F11 High Lift Configuration from HiLiftPW-2 using STAR-CCM+

Hanke, Jeremy L.; Shankara, P.; Snyder, Deryl O.

doi:10.2514/6.2014-0914

Cited by 6 publications

(6 citation statements)

References 8 publications

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“…STAR-CCM+ [10][11][12] is an unstructured cell-centered finite-volume-based solver. It was used for a variety of steady Reynolds-Averaged Navier-Stokes simulations.…”

Section: B Star-ccm+mentioning

confidence: 99%

Comparison of High-Fidelity Computational Tools for Wing Design of a Distributed Electric Propulsion Aircraft

Deere

Viken

Carter

et al. 2017

35th AIAA Applied Aerodynamics Conference

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A variety of tools, from fundamental to high order, have been used to better understand applications of distributed electric propulsion to aid the wing and propulsion system design of the Leading Edge Asynchronous Propulsion Technology (LEAPTech) project and the X-57 Maxwell airplane. Three highfidelity, Navier-Stokes computational fluid dynamics codes used during the project with results presented here are FUN3D, STAR-CCM+, and OVERFLOW. These codes employ various turbulence models to predict fully turbulent and transitional flow. Results from these codes are compared for two distributed electric propulsion configurations: the wing tested at NASA Armstrong on the Hybrid-Electric Integrated Systems Testbed truck, and the wing designed for the X-57 Maxwell airplane. Results from these computational tools for the high-lift wing tested on the Hybrid-Electric Integrated Systems Testbed truck and the X-57 high-lift wing presented compare reasonably well. The goal of the X-57 wing and distributed electric propulsion system design achieving or exceeding the required " = 3.95 for stall speed was confirmed with all of the computational codes. Nomenclature Symbols # drag coefficient a angle of attack, degrees #,%&'()* drag coefficient, pylons contribution Δ delta #,,-). drag coefficient, wing contribution #,/0 drag coefficient, tip nacelles contribution Acronyms #,10" drag coefficient, high-lift nacelles contribution BSL Menter kbasic turbulence model " lift coefficient CFL pseudo time advancement Courant-Friedrichs-Lewy ",344 effective lift coefficient: " + ",%5(% DEP distributed electric propulsion ",678 maximum lift coefficient HLN high-lift nacelles ",%5(% lift coefficient from the contribution of propeller thrust in lift direction KCAS KEAS knots calibrated airspeed knots equivalent airspeed 6

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“…STAR-CCM+ [10][11][12] is an unstructured cell-centered finite-volume-based solver. It was used for a variety of steady Reynolds-Averaged Navier-Stokes simulations.…”

Section: B Star-ccm+mentioning

confidence: 99%

Comparison of High-Fidelity Computational Tools for Wing Design of a Distributed Electric Propulsion Aircraft

Deere

Viken

Carter

et al. 2017

35th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

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“…Finally, a few observations and speculations as to the issue of accurately modeling stall. The following comments are based on the general workshop results, Rumsey, et al 4 , the AIAA SciTech 2014 presentations, 4,19,20,2122,23,24 and our current results. A number of contributors assessed the various effects of turbulence models, 4,19,20,22,23 transition, 4,21 time accuracy, 4,22 and a wide variety of solver approaches, grid refinements, and accuracy.…”

Section: Test Case 3 -Full Configuration Studymentioning

confidence: 95%

“…The 2 nd High Lift Prediction Workshop 4 (HiLiftPW-2) was held on June [22][23]2013 in San Diego, California. The basic objective of this workshop is to assess CFD methods using a high-lift configuration that is relevant to industry participants, challenging for grid generators and flow solvers and rich in publicly available data.…”

Section: Introductionmentioning

confidence: 99%

High Lift OVERFLOW Analysis of the DLR F11 Wind Tunnel Model

Pulliam

Sclafani

2014

32nd AIAA Applied Aerodynamics Conference

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In response to the 2 nd AIAA CFD High Lift Prediction Workshop, the DLR-F11 wind tunnel model is analyzed using the Reynolds -averaged Navier-Stokes flow solver OVERFLOW. A series of overset grids for a bracket-off landing configuration is constructed and analyzed as part of a general grid refinement study. This high Reynolds number (15.1 million) analysis is done at multiple angles -of-attack to evaluate grid resolution effects at operational lift levels as well as near stall. A quadratic constitutive relation recently added to OVERFLOW for improved solution accuracy is utilized for side-of-body separation issues at low angles-of-attack and outboard wing separation at stall angles. The outboard wing separation occurs when the slat brackets are added to the landing configuration and is a source of discrepancy between the predictions and experimental data. A detailed flow field analysis is performed at low Reynolds number (1.35 million) after pressure tube bundles are added to the bracket-on medium grid system with the intent of better understanding bracket/bundle wake interaction with the wing's boundary layer. Localized grid refinement behind each slat bracket and pressure tube bundle coupled with a time accurate analysis are exercised in an attempt to improve stall prediction capability. The results are inconclusive and suggest the simulation is missing a key element such as boundary layer transition. The computed lift curve is under-predicted through the linear range and over-predicted near stall, and the solution from the most complete configuration analyzed shows outboard wing separation occurring behind slat bracket 6 where the experiment shows it behind bracket 5. These results are consistent with most other participants of this workshop.

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“…We used the STAR-CCM+ ® (CD-adapco [Computational Dynamics Limited, United Kingdom, and Analysis & Design Application Co., United States]) polyhedral unstructured computational fluid dynamics (CFD) code 4 to conduct the wing stall analysis for an isolated ACTE wing on a symmetry plane at various ACTE flap deflections both in free air and in ground effect. The CFD methodology is next described.…”

Section: Figure 1 Solid Computer-aided Design Model Of the Adaptive Compliant Trailing Edge Airplanementioning

confidence: 99%

Analysis of Low-Speed Stall Aerodynamics of a Swept Wing with Seamless Flaps

Bui

2016

34th AIAA Applied Aerodynamics Conference

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Computational fluid dynamics (CFD) analysis was conducted to study the low-speed stall aerodynamics of a Gulfstream G-III airplane (Gulfstream Aerospace Corporation, Savannah, Georgia) swept wing modified with an experimental seamless, compliant flap called the Adaptive Compliant Trailing Edge (ACTE) flap. The stall characteristics of the modified ACTE wing were analyzed and compared with the unmodified, clean wing at the flight speed of 120 kn and altitude of 2300 ft above mean sea level, in free air as well as in ground effect. A polyhedral finite-volume unstructured full Navier-Stokes CFD code, STAR-CCM+ ® (CD-adapco [Computational Dynamics Limited, United Kingdom, and Analysis & Design Application Co., United States]), was used. Steady Reynolds-averaged Navier-Stokes CFD simulations were conducted for a clean wing and the ACTE wings at various ACTE deflection angles in free air (-2 deg, 15 deg, and 30 deg) as well as in ground effect (15 deg and 30 deg).Solution sensitivities to grid densities were examined. In free air, the ACTE wings are predicted to stall at lower angles of attack than the clean wing. In ground effect, all wings are predicted to stall at lower angles of attack than the corresponding wings in free air. Even though the lift curves are higher in ground effect than in free air, the maximum lift coefficients for all wings are lower in ground effect. Finally, the lift increase due to ground effect for the ACTE wing is predicted to be less than the clean wing. Nomenclature

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Numerical Simulation of DLR-F11 High Lift Configuration from HiLiftPW-2 using STAR-CCM+

Cited by 6 publications

References 8 publications

Comparison of High-Fidelity Computational Tools for Wing Design of a Distributed Electric Propulsion Aircraft

Comparison of High-Fidelity Computational Tools for Wing Design of a Distributed Electric Propulsion Aircraft

High Lift OVERFLOW Analysis of the DLR F11 Wind Tunnel Model

Analysis of Low-Speed Stall Aerodynamics of a Swept Wing with Seamless Flaps

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