年間 6 号発行
ISSN 印刷: 1948-2590
ISSN オンライン: 1948-2604
STUDY OF AERODYNAMICS OF THE AEROSPACE VEHICLE WITH A DEFLECTED BALANCING FLAP
要約
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.
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