F-5 Shaped Sonic Boom Demonstrator's Persistence of Boom Shaping Reduction Through Turbulence

Morgenstern, John M.; Arslan, Alan; Lyman, V.; Vadyak, J.

doi:10.2514/6.2005-12

Cited by 25 publications

(10 citation statements)

References 6 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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“…The predictions of the initial overpressure and signature duration are quite accurate, with about a 20 percent overestimate of the maximum and minimum overpressures in the ground signature (see Fig. 5b in [8]). More comparison results of CFD predictions and flight data at approximately 100 ft below the aircraft for the F-5E can be found in [9].…”

Section: Introductionmentioning

confidence: 91%

“…The flowpath and weight results from WATE++ are shown in Figure 2 and Table 2. Total installed weight, lb 8,197 Note that the MFTF optimization is decoupled from the mission, noise, and takeoff/landing analyses because of the primary focus on low-boom and low-drag properties of the concept in this study. Therefore, the engine generated by the current optimization process is not necessarily the most desirable engine at the system level.…”

Section: E Cycle Selection and Nacelle Geometry Definitionmentioning

confidence: 99%

Integration of Engine, Plume, and CFD Analyses in Conceptual Design of Low-Boom Supersonic Aircraft

Campbell

Geiselhart

et al. 2009

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

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This paper documents an integration of engine, plume, and computational fluid dynamics (CFD) analyses in the conceptual design of low-boom supersonic aircraft, using a variable fidelity approach. In particular, the Numerical Propulsion Simulation System (NPSS) is used for propulsion system cycle analysis and nacelle outer mold line definition, and a low-fidelity plume model is developed for plume shape prediction based on NPSS engine data and nacelle geometry. This model provides a capability for the conceptual design of low-boom supersonic aircraft that accounts for plume effects. Then a newly developed process for automated CFD analysis is presented for CFD-based plume and boom analyses of the conceptual geometry. Five test cases are used to demonstrate the integrated engine, plume, and CFD analysis process based on a variable fidelity approach, as well as the feasibility of the automated CFD plume and boom analysis capability.

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“…3 While it has been reported that the front shock reduction in a sonic boom can be realized empirically (4) , the rear expansion reduction has not been realized. So in order to investigate the capability of both the front shock and the rear expansion reduction computationally, |∆Pmax| and |∆Pmin| have been applied as independent objective functions in this study.…”

Section: Optimization Problem Definitionmentioning

confidence: 99%

Low-Boom and Low-Drag Optimization of the Twin Engine Version of Silent Supersonic Business Jet

Sato

Kumano

Yonezawa

et al. 2008

JFST

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Multi-Objective Optimization has been applied to a design problem of the twin engine concept for Silent Supersonic Business Jet (SSBJ). This problem aims to find main wing, body, tail wing and engine nacelle configurations, which can minimize both sonic boom and drag in a supersonic cruising flight. The multi-objective genetic algorithm (MOGA) coupled with the Kriging model has been used to globally and effectively search for optimal design candidates in the multi-objective problem. The drag and the sonic boom have been evaluated by the computational fluid dynamics (CFD) simulation and the waveform parameter method. As a result, the present optimization has successfully obtained low-boom and low-drag design candidates, which are better than the baseline design by more than 40 % regarding each performance. Moreover, the structure of design space has been visualized by the self-organizing map (SOM).

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F-5 Shaped Sonic Boom Demonstrator's Persistence of Boom Shaping Reduction Through Turbulence

Cited by 25 publications

References 6 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

Integration of Engine, Plume, and CFD Analyses in Conceptual Design of Low-Boom Supersonic Aircraft

Low-Boom and Low-Drag Optimization of the Twin Engine Version of Silent Supersonic Business Jet

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