Calculated and Measured Pressure Fields for an Aircraft Designed for Sonic-boom Alleviation

Lyman, V.; Morgenstern, John M.

doi:10.2514/6.2004-4846

Cited by 10 publications

(4 citation statements)

References 2 publications

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“…Solution adaptive methods have been shown to accurately and efficiently predict the near-field pressure disturbance. 15,[30][31][32][33] The current adjoint-based error estimation and adaption procedure is applied to to the 3-D Mach 1.26 inviscid flow over two tandem cones connected by a cylinder and a wind tunnel sting. This is a case taken from a 1965 NASA Langley Research Center experiment and analysis reported in Ref.…”

Section: Introductionmentioning

confidence: 99%

Application of Parallel Adjoint-Based Error Estimation and Anisotropic Grid Adaptation for Three-Dimensional Aerospace Configurations

Lee-Rausch

Park

Jones

et al. 2005

23rd AIAA Applied Aerodynamics Conference

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I. AbstractThis paper demonstrates the extension of error estimation and adaptation methods to parallel computations enabling larger, more realistic aerospace applications and the quantification of discretization errors for complex 3-D solutions. Results were shown for an inviscid sonic-boom prediction about a double-cone configuration and a wing/body segmented leading edge (SLE) configuration where the output function of the adjoint was pressure integrated over a part of the cylinder in the near field. After multiple cycles of error estimation and surface/field adaptation, a significant improvement in the inviscid solution for the sonic boom signature of the double cone was observed. Although the double-cone adaptation was initiated from a very coarse mesh, the near-field pressure signature from the finaladapted mesh compared very well with the wind-tunnel data which illustrates that the adjoint-based error estimation and adaptation process requires no a priori refinement of the mesh. Similarly, the near-field pressure signature for the SLE wing/body sonic boom configuration showed a significant improvement from the initial coarse mesh to the final adapted mesh in comparison with the wind tunnel results. Error estimation and field adaptation results were also presented for the viscous transonic drag prediction of the DLR-F6 wing/body configuration, and results were compared to a series of globally refined meshes. Two of these globally refined meshes were used as a starting point for the error estimation and field-adaptation process where the output function for the adjoint was the total drag. The field-adapted results showed an improvement in the prediction of the drag in comparison with the finest globally refined mesh and a reduction in the estimate of the remaining drag error. The adjoint-based adaptation parameter showed a need for increased resolution in the surface of the wing/body as well as a need for wake resolution downstream of the fuselage and wing trailing edge in order to achieve the requested drag tolerance. Although further adaptation was required to meet the requested tolerance, no further cycles were computed in order to avoid large discrepancies between the surface mesh spacing and the refined field spacing. II. IntroductionAs advanced computational fluid dynamics (CFD) codes have been developed to capture increasingly more complex flow features, assuring that the computational meshes are adequate to resolve these flow features has become a challenge. In aerospace applications, this can be especially difficult due to the wide range of speeds and conditions that must be simulated. A primary goal of CFD simulation is to accurately predict and understand wind tunnel and full-scale tests. Validation efforts have been applied to two-dimensional (2-D) and three-dimensional (3-D) problems to quantify current capabilities and expose deficiencies in current CFD simulation and wind tunnel testing practices. Both 2-D and 3-D validation efforts have been hampered by a number of factors including adequate...

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Section: Introductionmentioning

confidence: 99%

Application of Parallel Adjoint-Based Error Estimation and Anisotropic Grid Adaptation for Three-Dimensional Aerospace Configurations

Lee-Rausch

Park

Jones

et al. 2005

23rd AIAA Applied Aerodynamics Conference

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“…and then using these coefficients to obtain the corrected far-field using Equation 4. Following along similar lines, Lyman and Morgenstern [13] obtain the corrected far-field to a multipole order of 11. In the following sections, it is shown mathematically that the far field Fourier component, F ∞ n , can be obtained directly from its near field counterpart, F n , without having to calculate the multipole coefficients.…”

Section: Introductionmentioning

confidence: 86%

A New Approach for Incorporating Computational Fluid Dynamics into Sonic Boom Prediction

Rallabhandi

Mavris

2006

24th AIAA Applied Aerodynamics Conference

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“…It is more usual to measure the near-fi eld pressures then propagate these to ground level via a sonic boom propagation methodology, for example. 52,53 Whilst full-scale fl ight testing should provide the best source of data for rigorous validation of numerical or analytical prediction methods, in practice it usually contains some degree of uncertainty. Parameters that are diffi cult to determine include wind and temperature vertical distribution and atmospheric turbulence.…”

Section: Experimental Simulationmentioning

confidence: 99%

Innovation in supersonic passenger air travel

Smith

2012

Innovation in Aeronautics

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Calculated and Measured Pressure Fields for an Aircraft Designed for Sonic-boom Alleviation

Cited by 10 publications

References 2 publications

Application of Parallel Adjoint-Based Error Estimation and Anisotropic Grid Adaptation for Three-Dimensional Aerospace Configurations

Application of Parallel Adjoint-Based Error Estimation and Anisotropic Grid Adaptation for Three-Dimensional Aerospace Configurations

A New Approach for Incorporating Computational Fluid Dynamics into Sonic Boom Prediction

Innovation in supersonic passenger air travel

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