Conceptual Design of Low-Boom Aircraft with Flight Trim Requirement

Ordaz, Irian; Geiselhart, Karl; Fenbert, James W.

doi:10.2514/1.c033160

Cited by 35 publications

(11 citation statements)

References 13 publications

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“…The JWB design process is described by Ueno, Kanamori, and Makino [63]. The JWB is a wing body configuration designed to the same equivalent area target as the NASA Concept 25D [64]. The first phase of the design used Euler calculations and shape optimization to match the equivalent area target.…”

Section: B Jwbmentioning

confidence: 99%

Nearfield Summary and Statistical Analysis of the Second AIAA Sonic Boom Prediction Workshop

Park

Nemec

2019

Journal of Aircraft

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A summary is provided for the Second AIAA Sonic Boom Workshop held 8-9 January 2017 in conjunction with AIAA SciTech 2017. The workshop used three required models of increasing complexity: an axisymmetric body, a wing body, and a complete configuration with flow-through nacelle. An optional complete configuration with propulsion boundary conditions is also provided. These models are designed with similar nearfield signatures to isolate geometry and shock/expansion interaction effects. Eleven international participant groups submitted nearfield signatures with forces, pitching moment, and iterative convergence norms. Statistics and grid convergence of these nearfield signatures are presented. These submissions are propagated to the ground, and noise levels are computed. This allows the grid convergence and the statistical distribution of a noise level to be computed. While progress is documented since the first workshop, improvement to the analysis methods for a possible subsequent workshop are provided. The complete configuration with flow-through nacelle showed the most dramatic improvement between the two workshops. The current workshop cases are more relevant to vehicles with lower loudness and have the potential for lower annoyance than the first workshop cases. The models for this workshop with quieter ground noise levels than the first workshop exposed weaknesses in analysis, particularly in convective discretization. * Research Scientist, Computational AeroSciences Branch, Mike.Park@NASA.gov, AIAA Senior Member. † Aerospace Engineer, Computational Aerosciences Branch, Marian.Nemec@NASA.gov, AIAA Senior Member.

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Section: B Jwbmentioning

confidence: 99%

Nearfield Summary and Statistical Analysis of the Second AIAA Sonic Boom Prediction Workshop

Park

Nemec

2019

Journal of Aircraft

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“…It may also be possible to extend the trim-feasible target generation process that was presented in Ref. 2 for the under-track direction to account for the sonic boom at off-track directions.…”

Section: Design Procedures and Resultsmentioning

confidence: 99%

“…This approach is applied to the full-carpet design of a NASA-developed low-boom flight demonstrator concept. 2 The paper contains six sections, including the introduction section. Section II discusses the analysis, design, and optimization tools that are used during the design process.…”

Section: Introductionmentioning

confidence: 99%

Full-Carpet Design of a Low-Boom Demonstrator Concept

Ordaz

Wintzer

Rallabhandi

2015

33rd AIAA Applied Aerodynamics Conference

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The Cart3D adjoint-based design framework is used to mitigate the undesirable off-track sonic boom properties of a demonstrator concept designed for low-boom directly under the flight path. First, the requirements of a Cart3D design mesh are determined using a highfidelity mesh adapted to minimize the discretization error of the CFD analysis. Low-boom equivalent area targets are then generated at the under-track and one off-track azimuthal position for the baseline configuration. The under-track target is generated using a trimfeasible low-boom target generation process, ensuring that the final design is not only low-boom, but also trimmed at the specified flight condition. The off-track equivalent area target is generated by minimizing the A-weighted loudness using an efficient adjointbased approach. The configuration outer mold line is then parameterized and optimized to match the off-body pressure distributions prescribed by the low-boom targets. The numerical optimizer uses design gradients which are calculated using the Cart3D adjointbased design capability. Optimization constraints are placed on the geometry to satisfy structural feasibility. The low-boom properties of the final design are verified using the adaptive meshing approach. This analysis quantifies the error associated with the CFD mesh that is used for design. Finally, an alternate mesh construction and target positioning approach offering greater computational efficiency is demonstrated and verified.

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“…NASA recently developed an approach that couples these two design aspects, employing an adjoint-based inverse method to create a conceptual design tool [24][25][26] . This development effort has been very comprehensive and involves more than just being able to develop an OML based on a single point on the ground.…”

Section: Supersonicsmentioning

confidence: 99%

The Need for Advanced Simulations for Advanced Air Vehicle Concepts

Dryer¹,

Rogers

2016

46th AIAA Fluid Dynamics Conference

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A NASA program perspective is provided on the overall impact of advanced computational simulations on a portfolio of advanced air vehicles research. The current portfolio is built upon a rich history in both developing and employing advanced computational capabilities that enhance aerospace applications. These tools range from high-fidelity computational fluid dynamics simulations to comprehensive multidisciplinary design analysis and optimization codes. These analysis and design tools impact every area of vehicle-related research. Since this scope is so large, just a few representative examples from various aircraft and propulsion applications are provided. Brief assessments of potential future areas needing further development are also provided. In addition to using these tools to advance specific vehicle technologies, there are ongoing efforts to improve computational simulation capabilities in general by taking a long-term view of what key developments are needed in some key areas. Finally, a brief assessment is provided on how computational tools can be used more effectively in conjunction with ground and flight experimentation.

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Conceptual Design of Low-Boom Aircraft with Flight Trim Requirement

Cited by 35 publications

References 13 publications

Nearfield Summary and Statistical Analysis of the Second AIAA Sonic Boom Prediction Workshop

Nearfield Summary and Statistical Analysis of the Second AIAA Sonic Boom Prediction Workshop

Full-Carpet Design of a Low-Boom Demonstrator Concept

The Need for Advanced Simulations for Advanced Air Vehicle Concepts

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