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俄罗斯空气动力研究所中心学报

ISSN 打印: 1948-2590
ISSN 在线: 1948-2604

俄罗斯空气动力研究所中心学报

DOI: 10.1615/TsAGISciJ.v40.i5.10
pages 517-534

STUDY OF AERODYNAMICS OF THE AEROSPACE VEHICLE WITH A DEFLECTED BALANCING FLAP

A. V. Vaganov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Sergei Mikhailovich Drozdov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Sergey Mikhailovich Zadonsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Iraida Fedorovna Chelysheva
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Alexander Petrovich Kosykh
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Garry Grantovich Nersesov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Vladimir L'vovich Yumashev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia

ABSTRACT

Results of numeric modeling of three-dimensional flow around the configuration of the piloted orbital spaceship — the winged aerospace vehicle (ASV) proposed by the Central Hydrodynamic Institute [1−4] are presented and discussed in this paper. The flight vehicle with nondeflected control devices was examined in Ref. [4]. The effect of the deflection of the balancing flap on the flow field and the aerodynamic performance of the vehicle is studied here. The efficiency of the flap with its deflection from −5° to +10° is obtained. Computations were performed using the applied program package ARGOLA-2 for inviscid and thermally nonconductive gas within the range of incident flow Mach number from 1.1 to 16.5 and the angle of attack from zero to 45°. The effect of the real thermophysical properties of air on the aerodynamic performance of the winged ASV at hypersonic speed and the efficiency of the flap is estimated.