РЕЗУЛЬТАТИ ДОСЛІДЖЕННЯ РОЗПОДІЛУ СТАТИЧНОГО ТИСКУ НА ГОЛОВНІЙ ЧАСТИНІ РАКЕТНОГО АЕРОФІЗИЧНОГО КОМПЛЕКСА ТИПУ М-100 НА ОСНОВІ ЧИСЕЛЬНОГО МЕТОДУ РОЗРАХУНКУ І ЛЬОТНОГО ЕКСПЕРИМЕНТУ ДЛЯ ЧИСЕЛ MАХА ПОЛЬОТУ 1,4М4,2, РЕЙНОЛЬДСА ReL,  ≤108 , ПРИСКОРЕННЯ a ≤32g В УМОВАХ АЕРОДИНАМІЧНОГО НАГРІВУ

Abstract

Article is devoted to end-to-end solution of a problem of reliability and reliability of data on distribution of static pressure to surfaces of a head part of a missile M-100 aerophysical system in the range of Reynolds numbers of a flow , Mach numbers , an acceleration in flight conditions on a flight trajectory in the presence of aerodynamic heating, compressibility of a flow, effect of impact on the boundary layer of the operating engines by overcoming a problem of scale effects on the basis of the numerical solution of the equations of Navier-Stokes within a software product of ANSYS CFX and a flight experiment on a head part of a M-100 object. The problem of scale effects in aerodynamics of big speeds is discussed, the conclusion is drawn on special value of flight experiments in case of a trance- super- and hypersonic speeds, the review of algebraic, semi-differential and differential models of turbulence is provided and the conclusion is drawn on feasibility of use of model of turbulence of Menter. Calculation of static pressure on a head part of an object M-100 on the basis of the numerical solution of the equations of Navier-Stokes for the turbulent hyperacoustic mode of a flow is carried out. Good coordination of results of numerical calculation of static pressure and flight data. The comparative settlement data on pressure received by authors on the basis of some other methods are provided.