Langley Research Center Turbulence Modeling Resource

Exp: NASA Juncture Flow (JF) - Turbulent F6-Based Experimental Data

Return to: Exp: NASA Juncture Flow - Intro Page for Turbulent F6-Based Wing

Oil Flow Photos and Estimated Separation Sizes:

• OilFlow_update_2020.tar.gz (gzipped tar file, 34.1 MB)
• bubble_size_exp_F6_withhorn_2020.dat
• Note 1: Oil flow visualizations are generally regarded as qualitative in nature, so caution must be exercised when making use of the approximate measurements of mean corner-flow separation length and width.
• Note 2: In the experiment, the separation length was measured at the fuselage along the wing from the trailing edge to the approximate location of streamline departure. This is NOT the same as delta x, because the wing surface does not align with the x-axis. Roughly, L = (delta x)/[cos(17.5 deg)]. The separation width was measured along the trailing edge of the wing from the fuselage to the approximate location of the fluid (at the trailing edge) that emanated from the apex of separation. This is NOT the same as delta y, because the wing has dihedral and its surface does not align with the y-axis. Roughly, W = (delta y)/[cos(9.9 deg)].

LDV Data - Velocities, Reynolds Stresses, and Velocity Triple Products:

• LDV_Release_v6.tar.gz (gzipped tar file, 6.7 MB)

Model Pressures (F6-based wing with horn only):

• T653CpModelMeanData_2022.tar.gz (gzipped tar file, 2.3 MB) <- updated 8/19/2022*

Model Unsteady Surface Pressures:

• PSD_Release_v2.tar.gz (gzipped tar file, 37.9 MB)

PIV Data - Velocities and Reynolds Stresses:

• PIV_Data_v1.tar.gz (gzipped tar file, 15.3 MB)
• Auxiliary PIV data

* The newly posted Cp data now accounts for the total pressure deficit in the 14x22 tunnel. Taking total pressure into account causes a small change to the static pressure calculation, which in turn affects the Cp by a small shift. This shift is hardly noticeable when Cps are large (such as on the wing), but is noticeable - for example - at some fuselage stations where Cp magnitudes are small. Accounting for this deficit has a minimal effect on other tunnel conditions (such as Mach number, dynamic pressure, velocity, and Reynolds number).
 
 

Return to: Exp: NASA Juncture Flow - Intro Page for Turbulent F6-Based Wing

Recent significant updates:
08/19/2022 - posted an update to the Model Pressure data
11/18/2020 - posted V1 of PIV data
11/12/2020 - updated LDV data to V6
09/17/2020 - updated most of the experimental data to reflect additional results from Test 653

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Responsible NASA Official: Ethan Vogel
Page Curator: Clark Pederson
Last Updated: 08/19/2022