Home – Home – Jornals – Thermophysics and Aeromechanics 2003 number 2

The transonic regime of the flow around the airfoil is modelled in conditions of an pulse periodic energy. The objective of the present work is to study the effect of energy release on flow structure: decay and generation of shock waves, change of their position and strength as well as other effects caused by the flow reconstruction. The computed results are presented for the ideal gas flow around the airfoil NACA 0012 with the freestream Mach number of 0.8 for different locations of energy zones and values of the energy released. The flow was modelled on the basis of two-dimensional nonstationary gas dynamics equations. The stationary flow around the airfoil without the energy release was used as the initial condition. The explicit finite volume method diminishing the total variation (the TVD reconstruction) was used to find the numerical solution. The nonstationary problem was solved from the moment of time when the energy release is started up to obtaining a periodic regime. The possibilities are shown to control both the local and integral characteristics of airfoils at transonic flow regimes. A periodic character of the forming flow is established, which may be implemented at cruise flight speeds. The examples of both global and local flow reconstruction are presented.