Abstract
The article presents results of a numerical solution of subsonic and transonic flows described by the system of Navier-Stokes equations in 2D laminar compressible flows around the NACA 0012 airfoil. Authors used Runge-Kutta method to numerically solve the flows around the NACA 0012 airfoil.
Highlights
A numerical code has been developed for simulating transonic flow field around the NACA 0012 airfoil
The article presents results of a numerical solution of subsonic and transonic flows described by the system of Navier-Stokes equations in 2D laminar compressible flows around the NACA 0012 airfoil
1 Introduction A numerical code has been developed for simulating transonic flow field around the NACA 0012 airfoil. In these simulations the meshes type C has been used, which was created by mesh generator and has been described in [1,2]. In this case mesh has been created for numerical solution over profile NACA 0012
Summary
A numerical code has been developed for simulating transonic flow field around the NACA 0012 airfoil. In these simulations the meshes type C has been used, which was created by mesh generator and has been described in [1,2]. In this case mesh has been created for numerical solution over profile NACA 0012
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