• Corpus ID: 230438717

Performance of wall-modeled LES for external aerodynamics in the NASA Juncture Flow

@inproceedings{LozanoDuran2021PerformanceOW,
  title={Performance of wall-modeled LES for external aerodynamics in the NASA Juncture Flow},
  author={Adri'an Lozano-Dur'an and Sanjeeb T. Bose and Parviz Moin},
  year={2021}
}
The use of computational fluid dynamics (CFD) for external aerodynamic applications has been a key tool for aircraft design in the modern aerospace industry. CFD methodologies with increasing functionality and performance have greatly improved our understanding and predictive capabilities of complex flows. These improvements suggest that Certification by Analysis (CbA) –prediction of the aerodynamic quantities of interest by numerical simulations (Clark et al. 2020) may soon be a reality. CbA… 
Self-critical machine-learning wall-modeled LES for external aerodynamics
The use of computational fluid dynamics (CFD) for external aerodynamic applications has been a key tool for aircraft design in the modern aerospace industry. However, flow predictions from the
Performance of Wall-Modeled LES with Boundary-Layer-Conforming Grids for External Aerodynamics
B = intercept constant for the log law Cp = surface pressure coefficient L = crank chord, mm Nbl = point per boundary-layer thickness Npoints = total number of points of wall-modeled large-eddy

References

SHOWING 1-10 OF 29 REFERENCES
Self-critical machine-learning wall-modeled LES for external aerodynamics
The use of computational fluid dynamics (CFD) for external aerodynamic applications has been a key tool for aircraft design in the modern aerospace industry. However, flow predictions from the
CFD Analysis in Advance of the NASA Juncture Flow Experiment
NASA through its Transformational Tools and Technologies Project (TTT) under the Advanced Air Vehicle Program, is supporting a substantial effort to investigate the formation and origin of separation
Overflow Juncture Flow Computations Compared with Experimental Data
NASA’s Transformational Tools and Technologies Project (T ) is supporting a substantial effort to investigate the formation and origin of separation bubbles found on wing-body juncture zones: the
An Experimental Investigation of a Wing-Fuselage Junction Model in the NASA Langley 14- by 22-Foot Subsonic Wind Tunnel
Current turbulence models, such as those employed in Reynolds-averaged Navier-Stokes CFD, are unable to reliably predict the onset and extent of the three-dimensional separated flow that typically
Simulations of the NASA Langley 14- by 22-Foot Subsonic Tunnel for the Juncture Flow Experiment
NASA’s Transformational Tools and Technologies Program’s Juncture Flow experiment aims to provide data to improve Computational Fluid Dynamics (CFD) modeling in the juncture flow region. The
CFD Vision 2030 Study: A Path to Revolutionary Computational Aerosciences
This report documents the results of a study to address the long range, strategic planning required by NASA's Revolutionary Computational Aerosciences (RCA) program in the area of computational fluid
The NASA Juncture Flow Experiment: Goals, Progress, and Preliminary Testing (Invited)
NASA has been working toward designing and conducting a juncture flow experiment on a wing-body aircraft configuration. The experiment is planned to provide validation-quality data for CFD that
Goals and Status of the NASA Juncture Flow Experiment
The NASA Juncture Flow experiment is a new effort whose focus is attaining validation data in the juncture region of a wing-body configuration. The experiment is designed specifically for the purpose
Computational Aerodynamics Development and Outlook
TLDR
The field of computational fluid dynamics during recent years has developed sufficiently to initiate some changes in traditional methods of aerodynamic design, and numerical simulations offer the potential of mending many ills of wind-tunnel and turbomachinery experiments and of providing thereby important new technical capabilities for the aerospace industry.
Abridged Summary of the Third AIAA Computational Fluid Dynamics Drag Prediction Workshop
Results from the Third AIAA Drag Prediction Workshop (DPW-III) are summarized. The workshop focused on the prediction of both absolute and differential drag levels for wing-body and wing-alone
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