The article discusses a method for constructing an aircraft geometric shape for computing the parameters of aerogasdynamic flow as well as a method of meshing near the model to simulate the flow within the Navier–Stokes equations in the thin layer approximation. The results of the flow simulation are given. The calculations were performed on a multiprocessor computer system.
Bratchev A., Dubrovina A., Kotenev V., Maksimov F., Shevelev Y. Problem solution of aerodynamic design using multiprocessor computers. Маthematical Modeling and Coтputational Methods, 2015, №1 (5), pp. 17-30
The supersonic flows are implemented in an axisymmetric channel in many technical devices. These flows are in an expanding part of the nozzle or in the working part of supersonic wind tunnel. The method of supersonic flow calculation in an axisymmetric channel is developed. The method is based on the construction of multi-block axisymmetric grid and linearization of boundary conditions on the aerodynamic surfaces. Testing the method has showed good agreement with known experimental data. The method allows predicting the aerodynamic properties of the aerodynamic form, depending on its location in the channel, as well as the effect of the aerodynamic form on the channel walls in the channel.
Maksimov F. Supersonic flow in axisymmetric channel. Маthematical Modeling and Coтputational Methods, 2015, №1 (5), pp. 109-120