Langley Research Center Turbulence Modeling Resource

Exp: 2-D Coanda Airfoil with Tangential Wall Jet

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The data on this page were provided by K. Paschal.

These experimental data are for an airfoil with rounded (circular) trailing edge, over which a tangential jet is blown, causing reduced trailing edge flow separation due to the Coanda effect. The data were taken in the Basic Aerodynamic Research Tunnel (BART) at NASA Langley. Several different blowing coefficients were tested. (The jet blowing coefficient Cmu is defined by mdot*u_jet/(q_inf*S), where mdot is the jet mass flow rate, u_jet is the jet exit velocity, q_inf is freestream dynamic pressure, and S is the model chord times span.) Current documentation can be found in:

• Paschal, K. B., Neuhart, D. H., Beeler, G. B., and Allan, B. G., 2012. Circulation Control Model Experimental Database for CFD Validation. AIAA Paper 2012-0705, https://doi.org/10.2514/6.2012-705.

Some relevant information is given here, but the interested reader is referred to the above publication for complete details:

• Airfoil chord = 8.6 inches
• Airfoil thickness = 1.72 inches
• Airfoil span = 28 inches (spans the tunnel)
• Airfoil trailing edge radius = 0.817 inches
• Airfoil slot height = 0.020 inches
• Reference Re approximately 0.7 million per ft
• Reference Mach number = 0.1
• Airfoil angle of attack = 0
• Tunnel test section: 40 inches wide by 28 inches high

The geometry file describing the Coanda airfoil cross-section shape is here: Airfoil Definition.

Currently available experimental data are provided below. Note that the LDV data (velocity profiles) were taken in separate tests from the Cp data. Thus, there may be small differences in the conditions.

• Jet Momentum Blowing Coefficient Cmu approx 0.047:
  • Chordwise Cp
  • Spanwise Cp
  • Upper surface velocity and turbulence profiles at x/c=0.8
  • Upper surface velocity and turbulence profiles at x/c=0.9
  • Lower surface velocity and turbulence profiles at x/c=0.8
  • Lower surface velocity and turbulence profiles at x/c=0.9
• Jet Momentum Blowing Coefficient Cmu approx 0.114-0.115:
  • Chordwise Cp
  • Spanwise Cp
  • Upper surface velocity and turbulence profiles at x/c=0.8
  • Upper surface velocity and turbulence profiles at x/c=0.9
  • Lower surface velocity and turbulence profiles at x/c=0.8
  • Lower surface velocity and turbulence profiles at x/c=0.9
• Jet Momentum Blowing Coefficient Cmu approx 0.150:
  • Chordwise Cp
  • Spanwise Cp

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Last Updated: 07/06/2022