| Popis: |
There are presented the results of the main approaches analysis to modeling aerodynamic interference in the development of perspective aircrafts. The use of the methodological approaches proposed in the article will make it possible to determine the optimal aircraft layout in the formulation of the “wing-fuselage-engine” on the results of the achieved total aerodynamic characteristics. Analysis of modern armed conflicts shows that in most cases the use of aviation has a decisive influence on the outcome. Taking this into account, the main direction for the development of state aviation of Ukraine in the long term, with regard to the renewal of military transport aircraft fleet, is the designing and production of domestic planes. Nowadays, the world’s leading aircraft manufacturing companies (Airbus, Boeing and others) are working on the creation of competitive aircraft which are based on conceptually new schemes. This is because optimizing the shape of an aircraft can improve performance by only fraction of a percent while changes in the aircraft layout can lead to more significant positive results. Aerodynamic interference between the components of designed aircraft layout is relatively large and even minor changes in the geometry of one of the parts can significantly affect the overall aerodynamic characteristics of the aircraft. It is especially important to investigate the interference of working engines and airframe at different phases of flight at the stage of aircraft design. The purpose of the article is to present the results of the main approaches and methods analysis that can be used in modeling aerodynamic interference which is important in determining the total aerodynamic characteristics of advanced aircraft at the designing stage. This article uses the following research methods and methodologies: proven computational methods for optimizing the shape of an aircraft at the initial designing stage; boundary element methods, which are used to calculate potential flows, are also called methods of hydrodynamic singularities; numerical methods for studying the process of flow around bodies are used to study aero hydrodynamics based on various combinations of distributed and discrete hydrodynamic singularities; the numerical-analytical method and the panel method are used to calculate the carrier and moment characteristics of the airfoil in the framework of an ideal fluid; calculations based on the Navier-Stokes equations with a set of turbulence models are used for more complete and reliable information for calculating the carrier and moment characteristics of the airfoil; the discrete vortex method is used when the engine and the airframe are not considered separately from each other, but together; an iterative combination of the panel method with subsequent solution of the boundary layer equations for calculating the inviscid flow is used to take into account the effect of viscosity on the aerodynamic characteristics of the Conclusion: For solving problems of aerodynamic interference, the most suitable methods of the ideal fluid are the numerical-analytical and panel ones. More complete and reliable information on the calculation of the carrier and moment characteristics of the airfoil can be obtained by solving the full Navier-Stokes equations with a set of turbulence models. For those cases when it is necessary to obtain the aerodynamic characteristics of an aircraft that is designed with high accuracy.It is advisable to experimentally determine the corrections that are associated with the influence of operating engines. |
