Langley Research Center Turbulence Modeling Resource

Exp: NASA Juncture Flow (JF)

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These experimental data are for a full-span wing-body configuration, with a focus on the junction region (between the wing and fuselage) on the upper surface. Separated flow occurs near the trailing edge of the wing near the wing-root junction. Although other data were also taken, the main focus of the experiment was to document velocities and Reynolds stresses in the flowfield near and upstream of the junction region of interest. An on-board laser doppler velocimetry (LDV) system was used, which measured through windows on the port side of the fuselage (some of the tests also used on-board particle image velocimetry (PIV)). The primary goal was to provide information for validation and improvement of turbulence models, for predicting separated corner flows.

The first two experimental campaigns (Phases 1 and 2) were for a wing based on the DLR-F6 configuration, which produced separated corner flow at all angles of incidence tested. The Phase 3 test was conducted for a different (symmetric) wing with root shape based on the NACA 0015 airfoil. This wing was used to explore incipient separation; it yielded attached flow at some angles of incidence and a very small separation region at others. The Phase 3 test also included an investigation into natural transition on an untripped version of the wing. All tests used the same fuselage. The links for the experiments are provided below.

All data were taken in the NASA Langley 14-by-22 foot subsonic wind tunnel (often referred to on these pages as simply "14x22"). Phase 1 data were acquired from November 2017 through March 2018. Results were acquired both without and with a horn (a fillet or extension between the wing and body at the wing leading edge, whose purpose is to eliminate or lessen the strength/influence of the horseshoe vortex). Test 638 was without horn and Test 640 was with horn. Phase 2 data were taken in Test 653 (again on the F6-based wing with horn) in January through March 2020, with the purpose of expanding the F6-based wing "with horn" dataset and resolving some questions from the Phase 1 test. Phase 3 data were taken on the symmetric wing "with horn" in Test 662 in January through March 2022.

Documentation and data from the Juncture Flow project can be found in:

TURBULENT F6-BASED WING <- more corner separation

TURBULENT SYMMETRIC WING <- less corner separation (including incipient)

NATURAL TRANSITION ON SYMMETRIC WING
 

Papers:

• Kegerise, M. A., Leidy, A. N., Hannon, J. A., and Rumsey, C. L., "Measurements and Computational Analysis of the Turbulent Corner Flow on the NASA Juncture-Flow Model with a Symmetric Wing," NASA/TP-20240004000, April 2024.
• Kegerise, M. A., Leidy, A. N., Hannon, J. A., Rumsey, C. L., and Pulliam, T. H., "Measurements and Computations of the Turbulent Corner Flow on the NASA Juncture-Flow Model with a Symmetric Wing," AIAA-2023-0440, January 2023, doi: https://doi.org/10.2514/6.2023-0440.
• Leidy, A. N., Kegerise, M. A., Hannon, J. A., Choudhari, M. M., Venkatachari, B. S., and Paredes, P., "Measurements and Computations of Natural Transition on the NASA Juncture-Flow Model with a Symmetric Wing," AIAA-2023-0441, January 2023, doi: https://doi.org/10.2514/6.2023-0441.
• Rumsey, C. L., Ahmad, N. N., Carlson, J.-R., Kegerise, M. A., Neuhart, D. H., Hannon, J. A., Jenkins, L. N., Yao, C.-S., Balakumar, P., Gildersleeve, S., Bartram, S. M., Pulliam, T. H., Olsen, M. E., and Spalart, P. R., "NASA Juncture Flow Computational Fluid Dynamics Validation Experiment," AIAA Journal, Vol. 60, No. 8, 2022, pp. 4789-4805, doi: https://doi.org/10.2514/1.J061600.
• Rumsey, C. L., "Insights and Lessons Learned from the NASA Juncture Flow Experiment," AIAA Journal of Aircraft, Vol. 59, No. 6, 2022, pp. 1493-1499, doi: https://doi.org/10.2514/1.C036838.
• Venkatachari, B. S., Paredes, P., Choudhari, M., Li, F., and Chang, C.-L., "Pretest Computational Assessment of Boundary Layer Transition in the NASA Juncture Flow Model with an NACA 0015-Based Wing," AIAA-2021-2502, August 2021, doi: https://doi.org/10.2514/6.2021-2502.
• Rumsey, C. L., Ahmad, N. N., Carlson, J.-R., Kegerise, M. A., Neuhart, D. H., Hannon, J. A., Jenkins, L. N., Yao, C.-S., Balakumar, P., Gildersleeve, S., Bartram, S. M., Pulliam, T. H., Olsen, M. E., and Spalart, P. R., "CFD Comparisons with Updated NASA Juncture Flow Data," AIAA-2021-1427, January 2021, doi: https://doi.org/10.2514/6.2021-1427.
• Eisfeld, B., Rumsey, C. L., Togiti, V., Braun, S., and Sturmer, A., "Reynolds-Stress Model Computations of NASA Juncture Flow Experiment," AIAA Journal, Vol. 60, No. 3, 2022, pp. 1643-1662, doi: https://doi.org/10.2514/1.J060510.
• Ahmad, N. N., Rumsey, C. L., and Carlson, J.-R., "In-Tunnel Simulations of the NASA Juncture Flow Model," AIAA-2021-1428, January 2021, doi: https://doi.org/10.2514/6.2021-1428.
• Rumsey, C. L., Carlson, J.-R., Pulliam, T. H., and Spalart, P. R., "Improvements to the Quadratic Constitutive Relation Based on NASA Juncture Flow Data," AIAA Journal, Vol. 58, No. 10, 2020, pp. 4374-4384, doi: https://doi.org/10.2514/1.J059683.
• Rumsey, C. L., Lee, H. C., and Pulliam, T. H., "Reynolds-Averaged Navier-Stokes Computations of the NASA Juncture Flow Model Using FUN3D and OVERFLOW," AIAA-2020-1304, January 2020, doi: https://doi.org/10.2514/6.2020-1304.
• Kegerise, M. A. and Neuhart, D. H., "An Experimental Investigation of a Wing-Fuselage Junction Model in the NASA Langley 14- by 22-Foot Subsonic Tunnel," NASA/TM-2019-220286 (gzipped), June 2019. (note typo on p. 73: 0.670 m should be 0.630 m)
• Kegerise, M. A., Neuhart, D. H., Hannon, J. A., Rumsey, C. L., "An Experimental Investigation of a Wing-Fuselage Junction Model in the NASA Langley 14- by 22-Foot Subsonic Wind Tunnel," AIAA-2019-0077, January 2019, doi: https://doi.org/10.2514/6.2019-0077. (note typo on p. 5: 0.670 m should be 0.630 m)
• Jenkins, L. N., Yao, C.-S., Bartram, S. M., "Flow-Field Measurements in a Wing-Fuselage Junction Using an Embedded Particle Image Velocimetry System," AIAA-2019-0078, January 2019, doi: https://doi.org/10.2514/6.2019-0078.
• Rumsey, C. L., Carlson, J.-R., Ahmad, N. N., "FUN3D Juncture Flow Computations Compared with Experimental Data," AIAA-2019-0079, January 2019, doi: https://doi.org/10.2514/6.2019-0079.
• Lee, H. C., Pulliam, T. H., "Overflow Juncture Flow Computations Compared with Experimental Data," AIAA-2019-0080, January 2019, doi: https://doi.org/10.2514/6.2019-0080.
• Rumsey, C. L., "The NASA Juncture Flow Test as a Model for Effective CFD/Experimental Collaboration," AIAA-2018-3319, June 2018, doi: https://doi.org/10.2514/6.2018-3319.
• Lee, H. C., Pulliam, T. H., Rumsey, C. L., Carlson, J.-R., "Simulations of the NASA Langley 14- by 22- Foot Subsonic Tunnel for the Juncture Flow Experiment," NATO Science and Technology Organization, AVT-284 Research Workshop on Advanced Wind Tunnel Boundary Simulation, Torino, Italy, 16-18 April 2018, Paper Number STO-MP-AVT-284-02.
• Rumsey, C. L., Carlson, J.-R., Hannon, J. A., Jenkins, L. N., Bartram, S. M., Pulliam, T. H., Lee, H. C., "Boundary Condition Study for the Juncture Flow Experiment in the NASA Langley 14x22-Foot Subsonic Wind Tunnel," AIAA-2017-4126, June 2017, doi: https://doi.org/10.2514/6.2017-4126.
• Lee, H. C., Pulliam, T. H., Neuhart, D. H., and Kegerise, M. A., "CFD Analysis in Advance of the NASA Juncture Flow Experiment," AIAA-2017-4127 (gzipped), June 2017, doi: https://doi.org/10.2514/6.2017-4127.
• Kegerise, M. A. and Neuhart, D. H., "Wind Tunnel Test of a Risk-Reduction Wing/Fuselage Model to Examine Juncture-Flow Phenomena," NASA/TM-2019-219348, November 2016.
• Rumsey, C. L., Morrison, J. H., "Goals and Status of the NASA Juncture Flow Experiment," NATO Science and Technology Organization, Specialists' Meeting on Progress and Challenges in Validation Testing for Computational Fluid Dynamics, AVT-246-RSM-038, Avila, Spain, 26-28 September 2016, Paper Number STO-MP-AVT-246-03.
• Rumsey, C., Neuhart, D., and Kegerise, M., "The NASA Juncture Flow Experiment: Goals, Progress, and Preliminary Testing," AIAA Paper 2016-1557, January 2016, doi: https://doi.org/10.2514/6.2016-1557.

Slides:

• Rumsey, C. L., "The NASA Juncture Flow Experiment - Final Report," Rumsey oral presentation given at One NASA Boeing Team Meeting, March 2023.
• Rumsey, C. L., "Overview of the NASA Juncture Flow Project," Rumsey oral presentation given at AIAA SciTech in Orlando FL, January 2020.
• Kegerise, M. A., Neuhart, D. H., Hannon, J. A., and Rumsey, C. L., "Update on the NASA Junction-Flow Experiment: Methodology and Future Plans," Kegerise oral presentation given at AIAA Aviation in Dallas TX, June 2019. (typo correction 10/27/2020)
• Neuhart, D. H., Kegerise, M. A., Hannon, J. A., and Rumsey, C. L., "NASA Junction-Flow Experiment: Results and Future Plans," Neuhart oral presentation given at AIAA Aviation in Dallas TX, June 2019.
• Jenkins, L. N., Yao, C. S., and Bartram, S. M., "Update on Juncture Flow PIV," Jenkins oral presentation given at AIAA Aviation in Dallas TX, June 2019.
• Rumsey, C. L., "The NASA Juncture Flow Test as a Model for Effective CFD/Experimental Collaboration," Rumsey presentation given at AIAA Aviation in Atlanta GA, June 2018.

Special Session Papers:

To date, two AIAA Special Sessions on the JF (F6-based wing) have been conducted, one at SciTech 2020 and one at Aviation 2020. The papers are listed below; they are available from AIAA.

• AIAA-2020-1304 (Rumsey et al.): RANS with SA-based models - available above
• AIAA-2020-1305 (Abdol-Hamid et al.): RANS with k-kL-based models
• AIAA-2020-1306 (Eisfeld et al.): RANS with RSM models
• AIAA-2020-1307 (Iyer and Malik): WMLES
• AIAA-2020-1776 (Lozano-Duran et al.): WMLES
• AIAA-2020-1777 (Balin et al.): SA-based DDES
• AIAA-2020-1778 (Duda et al.): Lattice-Boltzmann
• AIAA-2020-2734 (Beyar et al.): Semispan JF experiment at CalTech, including some RANS results
• AIAA-2020-2735 (Ghate et al.): DDES and WMLES including targeted grid refinement
• AIAA-2020-2736 (Zastawny et al.): Zastawny: RANS including targeted grid refinement
• AIAA-2020-2750 (Aliaga et al.): RANS including grid adaption
• AIAA-2020-2751 (Wood et al.): RANS including grid adaption
• AIAA-2020-2752 (Abe et al.): RANS

Other Subsequent JF-Related Papers:

• AIAA-2021-0857 (Wang et al.): FUN3D iterative convergence improvements
• AIAA-2021-1429 (Olsen): Lag model
• AIAA-2021-1552 (Diskin et al.): Verification test suite for SA-QCR2000 model
• AIAA-2021-1743 (Duda and Laskowski): Lattice-Boltzmann
• AIAA-2022-3839 (Thomas and Agarwal): RANS models
• AIAA Journal, Vol. 60, No. 2, 2022 (pp. 747-766) (Lozano-Duran et al.): WMLES

14x22 high-speed leg geometry (empty tunnel):

• 14x22_highspeedleg_geometry.tar.gz

Return to: Data from Experiments - Intro Page

Recent significant updates:
09/20/2024 - added link to NASA/TP-20240004000
05/27/2022 - Added new sub-pages to more logically separate the various experiments
10/27/2020 - Note of typo in fuselage height in several references
07/02/2019 - Link to existing CFD grids and solutions completed
06/24/2019 - added slides from Aviation 2019
06/12/2019 - added link to NASA/TM-2019-220286

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Last Updated: 08/13/2025