Boundary Condition for Simulation of Flow Over Porous Surfaces

Neal, T Frink; Daryl, L Bonhaus; Veer, N Vatsa; Steven, X Bauer; Ana, F Tinetti

doi:10.2514/2.3147

Cited by 24 publications

(14 citation statements)

References 16 publications

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“…2c. The porosity factor σ, defined as the ratio between the open surface and the total surface, and the chordwise extent of the porous patch were selected based on the optimal configuration identified by Tinetti et al 9,10,17,18 The porous patch extended from the leading edge up to 10% chord. The porosity distribution followed a constant value of 0.22 for 0 < X/c < 0.05, after which the porosity decreased elliptically down to 0.10 for 0.05 < X/c < 0.10, with X the chordwise position from the leading edge and c the pylon chord.…”

Section: Methodsmentioning

confidence: 99%

Tractor Propeller-Pylon Interaction, Part II: Mitigation of Unsteady Pylon Loading by Application of Leading-Edge Porosity

Corte

Sinnige

Vries

et al. 2017

55th AIAA Aerospace Sciences Meeting

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Structure-borne noise can be a relevant source of cabin noise in advanced aircraft configurations with pylon-mounted tractor propellers. The periodic impingement of the propeller slipstream on the pylon causes unsteady loading that can be mitigated by applying passive porosity at the leading edge of the pylon. Pressure reconstruction from particle-image velocimetry was used to extract the unsteady pressure field around the pylon and the associated aerodynamic loads. Experimental results showed that porosity locally modifies the pylon near-wall pressure distribution because of the crossflow through the porous surface. Application of a porous leading edge reduced the intensity of the unsteady pressure fluctuations in the tip-vortex impingement region by approximately 5% and 30% on the suction and pressure sides of the pylon, respectively. Consequently, the unsteady pylon loading induced by the propeller tip vortices was reduced by 25%, thus resulting in a less intense source of vibrations. On the other hand, pylon drag was locally increased. Based on the experimental data, projections of the drag penalty were made for a generic pylon design. The resulting pylon drag penalty equaled 15% up to 35% for angles of attack of 0• up to 9• . This drag penalty was attributed to the early onset of transition caused by the increased surface roughness of the porous insert, and viscous dissipation of the crossflow through the cavity of the porous insert.

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Section: Methodsmentioning

confidence: 99%

Tractor Propeller-Pylon Interaction, Part II: Mitigation of Unsteady Pylon Loading by Application of Leading-Edge Porosity

Corte

Sinnige

Vries

et al. 2017

55th AIAA Aerospace Sciences Meeting

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“…The two-equation turbulence models were added to USM3D in the past few years mainly to meet the simulation requirements for propulsion airframe integration and high angle of attack flow conditions where shear layers, flow separation, and vortices are often the dominant components within the flow domain. Additional USM3D code features can be found in Frink et al and Pandya et al [23][24][25] …”

Section: A Usm3d Flow Solvermentioning

confidence: 99%

Unstructured CFD and Noise Prediction Methods for Propulsion Airframe Aeroacoustics

Pao

Abdol-Hamid

Campbell

et al. 2006

12th AIAA/CEAS Aeroacoustics Conference (27th AIAA Aeroacoustics Conference)

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Using unstructured mesh CFD methods for Propulsion Airframe Aeroacoustics (PAA) analysis has the distinct advantage of precise and fast computational mesh generation for complex propulsion and airframe integration arrangements that include engine inlet, exhaust nozzles, pylon, wing, flaps, and flap deployment mechanical parts. However, accurate solution values of shear layer velocity, temperature and turbulence are extremely important for evaluating the usually small noise differentials of potential applications to commercial transport aircraft propulsion integration. This paper describes a set of calibration computations for an isolated separate flow bypass ratio five engine nozzle model and the same nozzle system with a pylon. These configurations have measured data along with prior CFD solutions and noise predictions using a proven structured mesh method, which can be used for comparison to the unstructured mesh solutions obtained in this investigation. This numerical investigation utilized the TetrUSS system that includes a Navier-Stokes solver, the associated unstructured mesh generation tools, post-processing utilities, plus some recently added enhancements to the system. New features necessary for this study include the addition of two equation turbulence models to the USM3D code, an hrefinement utility to enhance mesh density in the shear mixing region, and a flow adaptive mesh redistribution method. In addition, a computational procedure was developed to optimize both solution accuracy and mesh economy. Noise predictions were completed using an unstructured mesh version of the JeT3D code.

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“…It contains the standard BCs of flow tangency or no-slip on solid surfaces, characteristic inflow/outflow for subsonic boundaries, and freestream inflow and extrapolation outflow for supersonic flow. It also contains some additional special BCs for jet exhaust and intake, a propeller/rotor actuator disk model, and passive porosity [19]. The most recent enhancements to USM3D are second-order time accuracy, Detached Eddy Simulation (DES) capability, dynamic grid motion [20], and overset-grid moving body capability [21].…”

Section: A Usm3d Flow Solvermentioning

confidence: 99%

Enhancement of USM3D Unstructured Flow Solver for High-speed High-Temperature Shear Flows

Pandya

Abdol-Hamid

Frink

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Boundary Condition for Simulation of Flow Over Porous Surfaces

Cited by 24 publications

References 16 publications

Tractor Propeller-Pylon Interaction, Part II: Mitigation of Unsteady Pylon Loading by Application of Leading-Edge Porosity

Tractor Propeller-Pylon Interaction, Part II: Mitigation of Unsteady Pylon Loading by Application of Leading-Edge Porosity

Unstructured CFD and Noise Prediction Methods for Propulsion Airframe Aeroacoustics

Enhancement of USM3D Unstructured Flow Solver for High-speed High-Temperature Shear Flows

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