Langley Research Center

Turbulence Modeling Resource

Exp: NASA Juncture Flow (JF) - Turbulent F6-based Wing

Return to: Exp: NASA Juncture Flow - Intro Page

Return to: Data from Experiments - Intro Page

Return to: Turbulence Modeling Resource Home Page

This is a sub-page of the NASA Juncture Flow (JF) website. The first JF experiments conducted (Phase 1 and 2) were on an F6-based wing. Details are provided here and on linked sub-pages below.
generic picture of JunctureFlow case: view near trailing edge juncture region generic picture of Juncture Flow case: no horn (Test 638) vs. horn (Test 640) shape

Some relevant information is given here for Tests 638 (F6-based configuration without horn), 640 (F6-based configuration with horn), and 653 (additional runs with the F6-based configuration with horn). (The flowfield information below actually comes directly from Test 640, but ranges for the other tests were very similar.) The interested reader is referred to the JF publications for complete details:

14x22 is a closed-circuit wind tunnel with air near sea level
Reynolds number was held fixed in the wind tunnel throughout the test; Re based on crank chord = 2.4 million (+-0.3%), or 4307.4515 per mm
Crank chord = 557.174 mm (the crank is the location of the break in the wing at around y=995.071 mm)
Nominal model incidence angles (deg) in tunnel (for the LDV data) = -2.5, +5.0, and +7.5 (ranges were -2.54 to -2.48, +4.97 to +5.04, and +7.48 to +7.53, respectively)
Mach number ranged from about 0.175 to 0.205 (nominally 0.189)
Temperature ranged from about 275 to 308 K (nominally 288.84 K)
Velocity ranged from about 58 to 72 m/sec (nominally 64.36 m/s)
Dynamic pressure ranged from about Q = 2107 to 2921 Pa (nominally 2476 Pa)
Boundary layers on fuselage and wing upper and lower surfaces were tripped
Fuselage length was nominally 4839.233 mm (190.521 inches)
Wing span tip-to-tip was nominally 3397.250 mm (133.750 inches), and the wing had dihedral
Leading edge wing sweep was approximately 27.1 degrees
Reference area used for F6-based wing with horn: 965543.23 mm² for semi-span model, 1931086.46 mm² for full-span model

TURBULENT F6-BASED GEOMETRY

TURBULENT F6-BASED BOUNDARY CONDITIONS

TURBULENT F6-BASED EXPERIMENTAL DATA

LINK TO EXISTING TURBULENT F6-BASED CFD GRIDS AND SOLUTIONS

Return to: Exp: NASA Juncture Flow - Intro Page

Return to: Data from Experiments - Intro Page

Return to: Turbulence Modeling Resource Home Page

Recent significant updates:
05/27/2022 - Made this a new subpage

Privacy Act Statement

Accessibility Statement

Responsible NASA Official: Ethan Vogel
Page Curator: Clark Pederson
Last Updated: 05/27/2022