Abstract

A numerical investigation of the adiabatic and condensing flow field around the ONERA M6 wing is performed. The fundamental equations are based on the compressible Navier-Stokes equations and three additional conservation equations for the liquid phase. Homogeneous nucleation and non-equilibrium condensation are modelled by the classical condensation theory. The Harten’s high-resolution TVD scheme is implemented for solving these equations. Three-dimensional transonic flows around the ONERA M6 wing under wind tunnel conditions are calculated by changing the relative humidity at three angles of attack, 1.07, 3.06 and 6.06 deg. The calculated results indicate that the onset of condensation is very sensitive to the angle of attack and the atmospheric humidity conditions. The condensation induces the release of latent heat and it directly affects the pressure coefficient distributions on the airfoil surface by increasing the humidity. Consequently, the lift-to-drag ratio of the airfoil is strongly influenced.

Keywords:

Moist air, non-equilibrium condensation, transonic flow,

References

Competing interests

The authors have no competing interests.

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Copyright

The authors have no competing interests.