Wind-US Flow Calculations for the M2129 S-duct Using Structured and Unstructured Grids

Mohler, Stanley R.

doi:10.2514/6.2004-525

Cited by 24 publications

(23 citation statements)

References 6 publications

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“…The different throat Mach numbers were a result of the set value of the outflow static pressure, and the downstream pressure ratios p=p 0 1 were those used by [14] Local time-stepping was used to integrate to a steady-state flowfield. The default second-order upwind-biased Roe scheme with modifications for stretched grids was used for the explicit right-hand side terms, and the default full block implicit scheme was used to compute the viscous terms.…”

Section: Computational Strategymentioning

confidence: 99%

Modeling Vortex Generators in a Navier-Stokes Code

Dudek

2011

AIAA Journal

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A source-term model that simulates the effects of vortex generators was implemented into the Wind-US NavierStokes code. The source term added to the Navier-Stokes equations simulates the lift force that would result from a vane-type vortex generator in the flowfield. The implementation is user-friendly, requiring the user to specify only three quantities for each desired vortex generator: the range of grid points over which the force is to be applied and the planform area and angle of incidence of the physical vane. The model behavior was evaluated for subsonic flow in a rectangular duct with a single vane vortex generator, subsonic flow in an S-duct with 22 corotating vortex generators, and supersonic flow in a rectangular duct with a counter-rotating vortex-generator pair. The model was also used to successfully simulate microramps in supersonic flow by treating each microramp as a pair of vanes with opposite angles of incidence. The validation results indicate that the source-term vortex-generator model provides a useful tool for screening vortex-generator configurations and gives comparable results to solutions computed using gridded vanes.

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Section: Computational Strategymentioning

confidence: 99%

Modeling Vortex Generators in a Navier-Stokes Code

Dudek

2011

AIAA Journal

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“…13. Note that the unstructured solutions were computed with the Spalart-Allmaras turbulence model on an unstructured grid with prismatic cells near solid surfaces and tetrahedral cells in the isotropic region, whereas the structured solutions were computed with the SST turbulence model.…”

Section: Resultsmentioning

confidence: 99%

“…The initial conditions for each case were the corresponding converged Wind-US baseline (i.e., no VGs) case at the same throat Mach number. The different throat Mach numbers were a result of the value of the outflow static pressure, and the downstream pressures were those used by Mohler 13 for the baseline case. For these simulations with the VGs specified, the following outflow pressures, 13.76, 12.86, 12.63, 12.34, and 12.11 psi, produced the respective corresponding throat Mach numbers, 0.4004, 0.6182, 0.6755, 0.7573, 0.8322.…”

Section: Computational Strategymentioning

confidence: 99%

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An Empirical Model for Vane-Type Vortex Generators in a Navier-Stokes Code

Dudek

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…The experimental analyses for the performance of only a baseline (clean) M2129 inlet were available; however, no validation data has been found for the icing cases. Also, the computational data for the baseline M2129 inlet using WIND-US code from [25] were provided for the comparison. For this validation, the size of the duct inlet was set based on the geometrical data from [20] and [25].…”

Section: Validation Of Numerical Solution 41 Baseline M2129 S-duct Imentioning

confidence: 99%

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

Jin¹,

Taghavi²,

Farokhi

2011

International Journal of Turbo and Jet Engines

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Abstract. The effect of flow angularity on an S-duct inlet with icing is computationally investigated. Flow angularity is simulated through angle-of-attack, and sideslip in addition to asymmetrical ice accretion on the inlet lip. A commercial CFD code, STAR-CCM+ is used for the steadystate computations with the shear-stress transport (SST) k-! turbulence model. Symmetrical and asymmetrical glaze ice shapes are computationally simulated on the inlet lip. The symmetrical glaze ice uniformly covers the entire cowl lip; whereas the asymmetrical glaze ice is simulated on a 1=4 sector of the inlet lip and is positioned on top, bottom or side of the inlet lip. The results indicate that flow angularity, whether in angle-of-attack or sideslip, aggravates the low performance of inlets with icing. The total pressure recovery suffers an additional 2% loss and the inlet mass flow rate drops by 7% when the inlet is at C20 ı angle of attack, as compared to zero angle, for flight Mach number of 0.34. The extent of loss in total pressure and a drop in mass flow rate depends on the asymmetrical icing location as well as the inlet angle-of-attack and sideslip. In addition, the ice-induced flow blockage is identified as a critical inlet performance parameter, since the symmetrical (360 ı ) glaze ice with its wider flow blockage creates a lower total pressure recovery than the asymmetrical (90 ı ) glaze ice at all angles of attack or sideslip.

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Wind-US Flow Calculations for the M2129 S-duct Using Structured and Unstructured Grids

Cited by 24 publications

References 6 publications

Modeling Vortex Generators in a Navier-Stokes Code

Modeling Vortex Generators in a Navier-Stokes Code

An Empirical Model for Vane-Type Vortex Generators in a Navier-Stokes Code

Asymmetrical Flow Simulation of Icing Effects in S-Duct Inlets at Angle of Attack

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