Simulation of transonic viscous flow over a fighter-like configuration including inlet

Flores, Jolen; Chaderjian, Neal M.; Sorenson, Reese L.

doi:10.2514/3.45759

Cited by 7 publications

(3 citation statements)

References 14 publications

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“…An F-16 is simulated with an active inlet as well as an active exhaust for demonstration. Specialized methods with the intent of capturing the effects of an active inlet on the pressure close to the inlet duct have been used for F-16 simulation in the past [1,10]. Based on these, a set of reference conditions that do not modify the conditions at the inlet are specified.…”

Section: B Two-shock Wedge Diffusermentioning

confidence: 99%

“…The assumption that power effects are minimal breaks down in a variety of well known circumstances. For example, the presence of an inlet that draws flow in or an exhaust with a substantial plume can have a noticeable effect on the flow field [1]. Flow features such as the thickness of the boundary layer, shock location and strength of a shock can be altered due to the presence of a plume.…”

Section: Introductionmentioning

confidence: 99%

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Validation of Inlet and Exhaust Boundary Conditions for a Cartesian Method

Pandya

Murman

Aftosmis

2004

22nd Applied Aerodynamics Conference and Exhibit

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Inlets and exhaust nozzles are often omitted in aerodynamic simulations of aircraft due to the complexities involved in the modeling of engine details and flow physics. However, the omission is often improper since inlet or plume flows may have a substantial effect on vehicle aerodynamics. A method for modeling the effect of inlets and exhaust plumes using boundary conditions within a n inviscid Cartesian flow solver is presented. T h i s a p proach couples with both CAD systems and legacy geometry to provide an automated tool suitable for parameter studies. The method is validated using tw* and three-dimensional test problems which are compared with both theoretical and experimental results. The numerical results demonstrate excellent agreement with theory and available data, even for extremely strong j e t s and very sensitive inlets.

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Section: B Two-shock Wedge Diffusermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Validation of Inlet and Exhaust Boundary Conditions for a Cartesian Method

Pandya

Murman

Aftosmis

2004

22nd Applied Aerodynamics Conference and Exhibit

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“…A comparison between single, two-, and three-zone flow computations is given in the Results section. For more details of the zonal grid procedure and interface boundary treatment see Flores et al 21…”

Section: Zonal Approachmentioning

confidence: 99%

Transonic Navier-Stokes computations for an oscillating wing using zonal grids

Chaderjian

Guruswamy

1992

Journal of Aircraft

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Modern jet transports and maneuvering tactical fighters operating in the transonic regime often give rise to time-dependent fluid physics that interact with flexible structural components, e.g., vortical flow, shocks, and separation. Efficient computational fluid dynamic methods are required to study such computationally intensive problems. A numerical method is presented to address this problem. Time-dependent, compressible, Navier-Stokes equations are used to simulate unsteady transonic flow about a three-dimensional rigid wing undergoing a forced periodic motion in angle of attack. An efficient, implicit, diagonal algorithm is utilized because of its low operation count per time step compared to other methods that solve systems of block matrix equations. The formal time accuracy is theoretically addressed and numerically demonstrated by comparison of computational results with experimental data. A zonal grid approach, capable of treating complex geometries, is presented and its time accuracy is demonstrated by comparing two-and three-zone computations with a single grid computation and experimental data.

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Calculation of laminar recirculating flows using a local non‐staggered grid refinement system

Coelho¹,

Pereira²,

Carvalho³

1991

Numerical Methods in Fluids

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SUMMARYA grid-embedding technique for the solution of two-dimensional incompressible flows governed by the Navier-Stokes equations is presented. A finite volume method with collocated primitive variables is employed to ensure conservation at the interfaces of embedding grids as well as global conservation. The discretized equations are solved simultaneously for the whole domain, providing a strong coupling between regions of different refinement. The formulation presented herein is applicable to uniform or non-uniform Cartesian meshes. The method was applied to the solution of two scalar transport equations, to cavity flows driven by body and shear forces and to a sudden plane contraction flow. The numerical predictions are compared with the exact solutions when available and with experimental data. The results show that neither the convergence rate nor the stability of the method is affected by the presence of embedded grids. Embedded grids provide a better distribution of grid nodes over the computational domain and consequently the solution accuracy was improved. The grid-embedding technique proved also that significant savings in computing time could be achieved.

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Simulation of transonic viscous flow over a fighter-like configuration including inlet

Cited by 7 publications

References 14 publications

Validation of Inlet and Exhaust Boundary Conditions for a Cartesian Method

Validation of Inlet and Exhaust Boundary Conditions for a Cartesian Method

Transonic Navier-Stokes computations for an oscillating wing using zonal grids

Calculation of laminar recirculating flows using a local non‐staggered grid refinement system

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