Numerical simulation of compound wings wind tunnel test for wig effect vehicle

This paper presents the comparison of numerical simulation results and wind tunnel experiment for compound WIG's wing. Numerical was performed in ANSYS Fluent software. The choice turbulence model computational mesh parameters, including resolution boundary layer, are substantiated. Comparison showed good convergence middle density about 7 million cells first layer height 0.0001 m. Additional study k-ε realizable k-ω SST models done. Its result founded much efficiency than takes less time ensures same accuracy. can be argued that selected parameters used to obtain aerodynamic characteristics various layout solutions "type C" WIG craft.