Near field Sonic Boom calculation of Benchmark Cases

Gan, Jiaye; Zha, Gecheng

doi:10.2514/6.2015-1252

Cited by 5 publications

(3 citation statements)

References 47 publications

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“…Although it was an artificial problem, not based on any particular application, it had an important impact on the field, focussing attention on the development of accurate and efficient methods for the basic equations. More specialized benchmarks followed, with examples from multi-phase flow [25], aeronautical flows [19], and aero-acoustics [28]. In these later works, the benchmarks were for multiphysics models.…”

Section: The Utility Of These Computational Benchmarksmentioning

confidence: 99%

High Accuracy Benchmark Problems for Allen-Cahn and Cahn-Hilliard Dynamics

Church¹,

Guo²,

Jimack³

et al. 2019

CICP

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There is a large literature of numerical methods for phase field models from materials science. The prototype models are the Allen-Cahn and Cahn-Hilliard equations. We present four benchmark problems for these equations, with numerical results validated using several computational methods with different spatial and temporal discretizations. Our goal is to provide the scientific community with a reliable reference point for assessing the accuracy and reliability of future software for this important class of problem.

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Section: The Utility Of These Computational Benchmarksmentioning

confidence: 99%

High Accuracy Benchmark Problems for Allen-Cahn and Cahn-Hilliard Dynamics

Church¹,

Guo²,

Jimack³

et al. 2019

CICP

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“…The in house high order accuracy CFD code FASIP, which is intensively validated with various 2D and 3D steady and unsteady flows including sonic boom cases of bodies of revolution(NASA, Lockheed Martin) and NASA's delta wing configuration provided by the 2014 AIAA Sonic Boom Work Shop [25,34,26,35,36,37,38,39], is utilized for the CFD analysis. To accurately capture shock waves and sonic boom, high order shock capturing schemes, including 3rd order MUSCL scheme [40], 3rd, 5th and 7th order WENO schemes and a finite compact scheme combining a shock detector and 6th order Padé scheme, are utilized in the code [37,38,39,41].…”

Section: Numerical Approachmentioning

confidence: 99%

Analysis of a Low Boom Supersonic Flying Wing Preliminary Design

Gan

Zha

2015

53rd AIAA Aerospace Sciences Meeting

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This paper presents the numerical analysis of a low boom supersonic bi-directional flying wing (SBiDir-FW) preliminary design to demonstrate the advantages of the concept. The mission requirements include cruise Mach number of 1.6, cruise altitude around 50kft, payload of 100 passengers, and a range of 4000nm. The gross takeoff weight is about 197kLb. The configuration is a flying wing symmetric about both the longitudinal and span axes. The sweep angle varies from 82 • at the very leading edge to 78 • at the tip. Two designs with same sweep angles and planform shapes are presented by varying airfoil meanline angle distributions to achieve different overpressure signatures and L/D ratios. The first design D82-78.4 achieves an L/D of 8.16, C L of 0.54, and the ground sonic boom noise level of 71.7PLdB. The second design D82-78.8 increases the C L and L/D with C L =0.60 and L/D = 8.54, while keeping a low level of ground sonic boom at 71.9PLdB by cruising at a little higher altitude of 52kft. A typical near field overpressure signature has a strong shock wave followed by a strong expansion in the overall process of expansion. The strong shockexpansion is mostly canceled out by themselves during the process of the wave propagation to ground. The designs indicate that the overpressure signature and aerodynamic efficiency are very sensitive and controllable by the variation of meanline angle distributions of the airfoils. This is an important relationship between the geometry parameters and the sonic boom/aerodynamic efficiency so that a design optimization strategy can be developed. All the designs with varied meanline angle distributions in this paper are conducted manually. With the encouraging results achieved so far, it is believed that the NASA's N+2 and N+3 goal to have ground sonic boom below 70PLdB for a supersonic civil transport is close to reach if a systematic design optimization is conducted.

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“…[15][16][17][18][19] The influence of viscous effects, turbulence models and higher order schemes has also been investigated. 20,21 In this paper, four benchmark cases including two axisymmetric body, a simple delta wing body and a full configuration includes fuselage, wing, tail, flow-through nacelles, and blade wing were computed with a RANS based flow solver to predicted the near field sonic boom signature. The influences of geometry tip rounding, grid size, turbulence model and spatial discretization schemes are investigated.…”

Section: Introductionmentioning

confidence: 99%

Near Field Sonic Boom Analysis with HUNS3D Solver

Wang

Ren

et al. 2017

55th AIAA Aerospace Sciences Meeting

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Accurate analysis of sonic boom pressure signature using Computational Fluid Dynamics (CFD) is still a challenging task. In this paper, four benchmark cases including two axisymmetric body, a simple delta wing body and a full configuration includes fuselage, wing, tail, flow-through nacelles, and blade wing were computed with a Reynold-averaged Navier-Stokes (RANS) based flow solver to predicted the near field sonic boom signature. The computed results from CFD agree well with the measured data in wind tunnel experiment. The effects of geometry equivalent radius, grid size, turbulence model and spatial discretization schemes are investigated and discussed. I.

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Near field Sonic Boom calculation of Benchmark Cases

Cited by 5 publications

References 47 publications

High Accuracy Benchmark Problems for Allen-Cahn and Cahn-Hilliard Dynamics

High Accuracy Benchmark Problems for Allen-Cahn and Cahn-Hilliard Dynamics

Analysis of a Low Boom Supersonic Flying Wing Preliminary Design

Near Field Sonic Boom Analysis with HUNS3D Solver

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