Mixed-Fidelity Approach for Design of Low-Boom Supersonic Aircraft

Li, Wu; Shields, Elwood; Geiselhart, Karl

doi:10.2514/1.c000228

Cited by 23 publications

(24 citation statements)

References 9 publications

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“…10 in Ref. 2 for the sonic-boom analysis of this configuration.) The same mixedfidelity design process that is given in Ref.…”

Section: Matching Reversed Equivalent Area To a Target For Low-bomentioning

confidence: 99%

“…The same mixedfidelity design process that is given in Ref. 2 (except that A e is replaced with A e,r ) is used here for volume shaping to tailor the overall shape of A e,r , while a three-level full-factorial DOE for three twist angles of the horizontal tail is used to modify the aft shape of A e,r .…”

Section: Matching Reversed Equivalent Area To a Target For Low-bomentioning

confidence: 99%

“…Steps (1) and (2), along with the analysis portion of step (3), have been implemented in ModelCenter 1 as a mixed-fidelity design process for low-boom supersonic concepts. 2 Case studies using this mixed-fidelity process have been documented in Refs. 2 and 3.…”

Section: Introductionmentioning

confidence: 99%

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Inverse Design of Low-Boom Supersonic Concepts Using Reversed Equivalent-Area Targets

Rallabhandi

2014

Journal of Aircraft

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A promising path for developing a low-boom configuration is a multifidelity approach that (1) starts from a low-fidelity low-boom design, (2) refines the low-fidelity design with computational fluid dynamics (CFD) equivalent-area (A e ) analysis, and (3) improves the design with sonic-boom analysis by using CFD off-body pressure distributions. The focus of this paper is on the third step of this approach, in which the design is improved with sonicboom analysis through the use of CFD calculations. A new inverse design process for offbody pressure tailoring is formulated and demonstrated with a low-boom supersonic configuration that was developed by using the mixed-fidelity design method with CFD A e analysis. The new inverse design process uses the reverse propagation of the pressure distribution (dp/p) from a mid-field location to a near-field location, converts the near-field dp/p into an equivalent-area distribution, generates a low-boom target for the reversed equivalent area (A e,r ) of the configuration, and modifies the configuration to minimize the differences between the configuration's A e,r and the low-boom target. The new inverse design process is used to modify a supersonic demonstrator concept for a cruise Mach number of 1.6 and a cruise weight of 30,000 lb. The modified configuration has a fully shaped ground signature that has a perceived loudness (PLdB) value of 78.5, while the original configuration has a partially shaped aft signature with a PLdB of 82.3. Nomenclature

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“…10 in Ref. 2 for the sonic-boom analysis of this configuration.) The same mixedfidelity design process that is given in Ref.…”

Section: Matching Reversed Equivalent Area To a Target For Low-bomentioning

confidence: 99%

Section: Matching Reversed Equivalent Area To a Target For Low-bomentioning

confidence: 99%

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Inverse Design of Low-Boom Supersonic Concepts Using Reversed Equivalent-Area Targets

Rallabhandi

2014

Journal of Aircraft

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“…This baseline configuration is the result of earlier optimization using mixed-fidelity, 26 reversed-equivalent-area 22 methods. The initial mesh for this concept was generated using VGRID, 27 SSGRID 28 and is shown in Figure 2.…”

Section: Initial Mesh and Geometry Parameterizationmentioning

confidence: 99%

Sonic-Boom Mitigation Through Aircraft Design and Adjoint Methodology

Rallabhandi

Nielsen

Diskin

2014

Journal of Aircraft

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This paper presents a novel approach to design of the supersonic aircraft outer mold line (OML) by optimizing the A-weighted loudness of sonic boom signature predicted on the ground. The optimization process uses the sensitivity information obtained by coupling the discrete adjoint formulations for the augmented Burgers Equation and Computational Fluid Dynamics (CFD) equations. This coupled formulation links the loudness of the ground boom signature to the aircraft geometry thus allowing efficient shape optimization for the purpose of minimizing the impact of loudness. The accuracy of the adjoint-based sensitivities is verified against sensitivities obtained using an independent complex-variable approach. The adjoint based optimization methodology is applied to a configuration previously optimized using alternative state of the art optimization methods and produces additional loudness reduction. The results of the optimizations are reported and discussed.

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“…The current analysis and design process 4,5 for supersonic concepts at NASA Langley Research Center uses an automated USM3D 6, 7 CFD analysis to conduct high-fidelity aerodynamics analysis. This automated mesh generation and CFD analysis requires several hours to obtain off-body pressures for a conceptual configuration.…”

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confidence: 99%

Integration of Off-Track Sonic Boom Analysis in Conceptual Design of Supersonic Aircraft

Ordaz

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A highly desired capability for the conceptual design of aircraft is the ability to rapidly and accurately evaluate new concepts to avoid adverse trade decisions that may hinder the development process in the later stages of design. Evaluating the robustness of new low-boom concepts is important for the conceptual design of supersonic aircraft. Here, robustness means that the aircraft configuration has a low-boom ground signature at both under-and off-track locations. An integrated process for off-track boom analysis is developed to facilitate the design of robust low-boom supersonic aircraft. The integrated off-track analysis can also be used to study the sonic boom impact and to plan future flight trajectories where flight conditions and ground elevation might have a significant effect on ground signatures. The key enabler for off-track sonic boom analysis is accurate computational fluid dynamics (CFD) solutions for off-body pressure distributions. To ensure the numerical accuracy of the off-body pressure distributions, a mesh study is performed with Cart3D to determine the mesh requirements for offbody CFD analysis and comparisons are made between the Cart3D and USM3D results. The variations in ground signatures that result from changes in the initial location of the near-field waveform are also examined. Finally, a complete under-and off-track sonic boom analysis is presented for two distinct supersonic concepts to demonstrate the capability of the integrated analysis process. Symbols dp/p = near-field waveform

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Mixed-Fidelity Approach for Design of Low-Boom Supersonic Aircraft

Cited by 23 publications

References 9 publications

Inverse Design of Low-Boom Supersonic Concepts Using Reversed Equivalent-Area Targets

Inverse Design of Low-Boom Supersonic Concepts Using Reversed Equivalent-Area Targets

Sonic-Boom Mitigation Through Aircraft Design and Adjoint Methodology

Integration of Off-Track Sonic Boom Analysis in Conceptual Design of Supersonic Aircraft

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