Conditions for simulation of transonic flutter of aerodynamic control surfaces of supersonic aircraft in wind tunnels

The transonic flutter of the aerodynamic control surfaces supersonic and hypersonic aircraft refers to those phenomena dynamic aeroelasticity, assessment whichin a flight experiment is dangerous. Since there still no universally accepted mathematical model occurrence this phenomenon, tests dynamic-like models in wind tunnels can be classified as basic safe methods for evaluating characteristics flutter. Therefore, substantiation conditions modeling flutter, which allow transfer results blowing full-scale designs, remains an actual scientific problem.The article proposes one possible approaches justifying tunnels, based on analysis nonlinear phenomenon.Based model, it was determined that, addition are due geometric similarity system "carrying surface – surface", additional phenomenon should following dimensionless quantities nature model:- amplitudes oscillations model;- numbers M at occurs;- logarithmic decrements surfaces;- Strouhal numbers;- ratio gas density material adiabatic index k=1.405, that is, working body tunnel air.Blowing dynamically similar must carried out continuous type, subject (s-1).