We consider the flow around the axisymmetric supersonic vehicle with the use of gas jetblowingfrom the lateral surface. The blowing is made in series of points at different distances from the nose fairing. The aim of the work was to determine the changes in aerodynamic forces and the formation of the moment, when jet of gasblowingin different parts of the supersonic vehicle. The study was conducted by numerical modeling of different cases of injection. As a result, data were obtained which showed the degree of influence not only jet thrust from the jet flow, but same the impact of the redistribution of the flow by body surface on the formation of aerodynamic forces and moments.
Рассмотрено влияние выдува газовой струи на аэродинамику летательного аппарата осесимметричной конфи-гурации и элементы его конструкции при сверхзвуковых скоростях полета. В качестве объекта исследования рассмат-ривались классические конфигурации, состоящие из конического головного обтекателя и корпуса в виде цилиндриче-ского тела с шестью консолями хвостового стабилизатора. В одном из рассмотренных вариантов конфигураций присут-ствовали дополнительные крылья, располагавшиеся сразу за отверстием выдува вниз по потоку. Был проведен анализ физической картины обтекания при выдуве поперечной газовой струи и получены степени влияния выдува на аэроди-намические характеристики корпуса и консолей хвостового стабилизатора. В качестве основных критериев оценки вно-симых изменений использовались коэффициенты лобового сопротивления, подъемной силы и момента тангажа. Ис-следование осуществлялось путем численного моделирования. Расчеты обтекания с выдувом поперечной газовой струи и без него выполнены при числе Маха набегающего потока М = 3 под углом атаки α = 0° на основе осредненных уравнений Навье-Стокса и SST k-ω модели турбулентности. При моделировании истечения струи задавались значения избыточного давления в соответствии с коэффициентом нерасчетности, составляющим примерно n = 10 2 , а также чис-ло Маха М = 1.Ключевые слова: сверхзвуковая скорость, численное моделирование, осесимметричный летательный аппа-рат, выдув газовой струи, аэродинамические характеристики.
V.A. Kislovsky, V.I. ZvegintsevKhristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch of Russian Academy of Sciences, Novosibirsk, Russian Federation
NUMERICAL SIMULATION OF THE EFFECT OF BLOWING A GAS JET ON AERODYNAMIC CHARACTERISTICS OF VEHICLE WITH AN AXISYMMETRIC CONFIGURATION WITH A TAIL STABILIZERThe effect of blowing a gas jet on the aerodynamics of vehicle with an axisymmetric configuration and elements this construction at supersonic flight velocity is considered. As the object of study, classical configurations of vehicle consisting of a conical head fairing and a body in the cylindrical form with six consoles of the tail stabilizer were considered. In one of the considered configurations variants, additional wings were located immediately behind the blowing hole in the downstream. An analysis of the physical flow pattern was carried out during the transverse gas jet blowing and the degree of blowing influence on the aerodynamic characteristics the hull and consoles of the tail stabilizer was obtained. As the main criteria for assessing the changes introduced, coefficients of drag, lift and pitch moment were used. The study was carried out by numerical simulation. Flow calculations, with and without a transverse gas jet blowing, are performed with the Mach number of the free stream M = 3 at an angle of attack α = 0 ° on the basis of the averaged Navier-Stokes equations and the SST k-ω turbulence model. Modeling the jet, the values of the excess pressure were set, in accordance with the pressure ratio coefficient, which is appr...
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