Langley Research Center Turbulence Modeling Resource

Exp: NASA Juncture Flow (JF) - Natural Transition on Symmetric Wing

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This is a sub-page of the NASA Juncture Flow (JF) website. These data are from the Phase 3 TRANSITIONAL testing on a symmetric wing shape. The boundary layers on the wing upper and lower surfaces were not tripped for this portion of the campaign. The wing itself is a blend of NACA 0015 at the root, NACA 0012 mid-span, and NACA 0010 near the tip. The wing also includes 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). This symmetric wing produces a much smaller separation than on the F6-based wing.

Some relevant information is given here.

• 14x22 is a closed-circuit wind tunnel with air near sea level
• Reynolds number was held fixed in the wind tunnel throughout the transition part of the test at 2.4 million (+-0.30%) based on crank chord¹
• Crank chord = 580.716 mm (the crank is the location of the break in the wing at around y=869.693 mm) (different than for the F6-based wing)¹
• Nominal model incidence angles (deg) in tunnel (for the IR data) ranged from -10 to 10 (+-0.02) in 2.5-deg increments, from -10 to 10 (+-0.02) in 1-deg increments, and -6 to -2 (+-0.02) in 0.25-deg increments
• Nominal model incidence angles (deg) in tunnel (for the Cp data used to determine transition location) ranged from -2 to 8 (+-0.02) in 1-deg increments
• Mach number in the transition part of the test ranged from about 0.174 to 0.192 (nominally² 0.189)
• Temperature in the transition part of the test ranged from about 282 to 300 K (nominally² 288.84 K)
• Velocity in the transition part of the test ranged from about 58 to 67 m/sec (nominally 64.4 m/s)
• Dynamic pressure in the transition part of the test ranged from about Q = 2115 to 2530 Pa (nominally 2385 Pa)
• Fuselage was the same used with the F6-based wing; length was nominally 4839.233 mm
• Wing span tip-to-tip was nominally 3326.932 mm, and the wing had no dihedral; the entire configuration was top-bottom symmetric (different than for the F6-based wing)
• Leading edge wing sweep was approximately 37.3 degrees (different than for the F6-based wing)
• Reference area used for symmetric wing with horn: 903701.52 mm² for semi-span model, 1807403.04 mm² for full-span model (different than for the F6-based wing)

¹Because the crank chord was different between the F6-based wing and the symmetric wing, the Reynolds number per mm was different ( 4307.4515 for the F6-based wing and 4132.8291 for the symmetric wing ).
²For the purpose of maintaining some consistency between input parameters for nondimensional CFD codes, the nominal M and T were chosen to be the same between the F6 and symmetric wing (because they were both well within the ranges experienced during each test). However, note that the velocity and Q end up to be somewhat different for the two wings because of the different unit Reynolds numbers.
 

TRANSITIONAL SYMMETRIC WING GEOMETRY

TRANSITIONAL SYMMETRIC WING BOUNDARY CONDITIONS

TRANSITIONAL EXPERIMENTAL DATA

LINK TO EXISTING TRANSITIONAL SYMMETRIC WING CFD GRIDS AND SOLUTIONS (not available yet)
 

Return to: Exp: NASA Juncture Flow - Intro Page

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Responsible NASA Official: Ethan Vogel
Page Curator: Clark Pederson
Last Updated: 04/07/2023