In this paper, rarefied supersonic gas flow around a NACA 0012 airfoil is studied using both continuum and particle solvers.Navier Stokes equations subject to first order slip/jump boundary conditions are solved under the framework of OpenFOAM package. The DSMC solver of the package, i.e., dsmcFoam,has been improved to includenewly presented “simplified Bernoulli Trial (SBT)” scheme for inter-molecular collision modeling. We considered flow at different angle of attack and Knudsen number.The computed density and surface pressure distribution are compared with the experimental and numerical data and suitable accuracy was observed. The main focus of this work is investigation of lift and drag coefficients variations with Knudsen number and angle of attack. At low angles of attack, our results for lift coefficient agree well with the linearized theory, however, the deviation starts as soon as angle of attack goes beyond 15◦. We observed that drag force increased as soon as Kn number increased. We alsoinvestigated the effect of Kn number on the leading edge shock position and structure, drag polar (CL/CD), and slip velocity over the airfoil.

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