Overview and Summary of the Third AIAA High Lift Prediction Workshop

Rumsey, Christopher L.; Slotnick, Jeffrey P.; Sclafani, Anthony

doi:10.2514/1.c034940

Cited by 135 publications

(31 citation statements)

References 45 publications

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“…Strong code-to-code agreement is observed for both the integrated quantities and the flow fields for the entire alpha sweep despite the tendency for steady-state RANS to bifurcate in regions of separated flow. Indeed the differences in CFD solutions become more pronounced post-stall, but the relative error between the codes is well within acceptable bounds as compared to the High Lift Prediction Workshop scatter in the stall regime [21]. These results are especially encouraging due to the fact that entirely different mesh paradigms and CFD solvers have independently predicted pre-stall and post-stall flow characteristics.…”

Section: Applying Lessons Learned To An Aerodynamic Databasementioning

confidence: 68%

Establishing Best Practices for X-57 Maxwell CFD Database Generation

Duensing

Yoo

Maldonado

et al. 2019

AIAA Scitech 2019 Forum

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The X-57 Maxwell is NASA's latest electric airplane concept that has been simulated for aerodynamic performance using the structured overset and unstructured grid solvers within the Launch Ascent and Vehicle Aerodynamics (LAVA) solver framework as well as the unstructured polyhedral grid solver in Star-CCM+ for code-to-code comparison. In order to validate the predictions, comparisons were made between the CFD solutions and experimental data collected in the 12-foot Low-Speed Wind Tunnel at NASA Langley Research Center. The simulations are in preparation for the development of a comprehensive aerodynamic database which will assess aircraft performance at a variety of conditions. The findings from these simulations will establish the best practices for mesh resolution, numerical discretization, and turbulence modeling to be used for this database. Preliminary database results have shown that best-practices learned from the initial validation simulations will potentially reduce error in X-57 aerodynamic loads and moments relative to experiment by up to 14%.

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Section: Applying Lessons Learned To An Aerodynamic Databasementioning

confidence: 68%

Establishing Best Practices for X-57 Maxwell CFD Database Generation

Duensing

Yoo

Maldonado

et al. 2019

AIAA Scitech 2019 Forum

View full text Add to dashboard Cite

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“…The gridding guidelines from the third American Institute of Aeronautics and Astronautics (AIAA) CFD High Lift Prediction Workshop are used to generate different grids in four levels: coarse, medium, fine, and extra-fine. 45 A super-fine grid level is added. The chordwise spacing at the leading edge (LE), , and trailing edge (TE), , are varied between 1 and 0.001% .…”

Section: Geometry Definition and Grid Resolution Studymentioning

confidence: 99%

Improved Mars Helicopter Aerodynamic Rotor Model for Comprehensive Analyses

2019

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The Mars Helicopter is part of the NASA Mars 2020 rover mission scheduled to launch in July of 2020. Its goal is to demonstrate the viability and potential of heavier-than-air vehicles in the Martian atmosphere. Ultimately, it aims to bridge the resolution gap between orbiters and the rover as well as allow access to otherwise inaccessible regions. The low density of the Martian atmosphere and the relatively small-scale rotor result in very low Reynolds number flows. The low density and low Reynolds numbers reduce the lifting force and lifting efficiency, respectively. This paper describes the generation of the improved Mars Helicopter aerodynamic rotor model. The goal is to generate a performance model for the Mars Helicopter rotor using a free wake analysis, since this has a low computational cost for design. The improvements in the analysis are two-fold and are expanded on from two prior publications. First, the fidelity of the simulations is increased by performing higher-order two-dimensional time-accurate OVERFLOW simulations allowing for higher accuracy aerodynamic coefficients and a better understanding of the boundary layer behavior as well as its transient features. Second, a version of the model is generated to duplicate the exact testing conditions in the 25-ft. diameter Space Simulator at the Jet Propulsion Laboratory, which allows for better correlation of rotor performance figures. Previous work correlated performance with that test, but did not consider the higher temperatures in the experiment compared to those of the Martian atmosphere. The higher temperatures in the experiment are expected to give conservative performance estimates, as they give rise to an increase in speed of sound and decrease in observed Reynolds numbers.

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“…Computational fluid dynamics (CFD) technology has made tremendous progress [2][3][4]; it has advantages in that not only can it reduce capital investment and maintenance costs, but it also can acquire physical quantity at any position in a computational domain. However, to realize accurate aerodynamic performance prediction for control devices, CFD is not mature yet; we deepen the perception of knowledge through the American Institute of Aeronautics and Astronautics high-lift prediction workshops [5][6][7]. On the other hand, in the wind tunnel test, we can obtain spatial data through particle image velocimetry (PIV) [8] measurements; we can comprehensively gain surface pressure/temperature through the invention and development of Pressure/Temperature Sensitive Paint (PSP/TSP) [9].…”

Section: Introductionmentioning

confidence: 99%

Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement

et al. 2020

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We have developed a remote and precise feedback control system using optical measurement technology to alter the angle of a flap, which is part of a wind tunnel test model, automatically and to earn the aerodynamic data efficiently. To rectify the wasteful circumstance that Japan Aerospace Exploration Agency (JAXA)’s low-turbulence wind tunnel stops ventilation every time to switch model configurations, we repaired hardware for remote operation and generated software for feedback control. As a result, we have accomplished a system that dramatically advances the efficiency of wind tunnel tests. Moreover, the system was able to consider the deformation of the model through optical measurement; the system controlled flap angles with errors less than the minimum resolution of optical measurement equipment. Consequently, we successfully grasped the nonlinearity of three aerodynamic coefficients C L , C D , and C M p that was impossible so far.

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Overview and Summary of the Third AIAA High Lift Prediction Workshop

Cited by 135 publications

References 45 publications

Establishing Best Practices for X-57 Maxwell CFD Database Generation

Establishing Best Practices for X-57 Maxwell CFD Database Generation

Improved Mars Helicopter Aerodynamic Rotor Model for Comprehensive Analyses

Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement

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