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

Volumen 40, Edición 5, 2009, pp. 517-534
DOI: 10.1615/TsAGISciJ.v40.i5.10
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SINOPSIS

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.

CITADO POR
  1. Titarev Vladimir, Dumbser Michael, Utyuzhnikov Sergey, Construction and comparison of parallel implicit kinetic solvers in three spatial dimensions, Journal of Computational Physics, 256, 2014. Crossref

  2. Titarev Vladimir, Software Package Nesvetay-3D for Modeling Three-Dimensional Flows of Monatomic Rarefied Gas, Science and Education of the Bauman MSTU, 14, 06, 2014. Crossref

  3. Zhang Yuling, Zhao Jieliang, Chen Weihua, Guo Xiaodong, Yan Shaoze, Hu Guotun, Yuan Yuan, Guo Pengfei, Cai Qiaoyan, Biomimetic skeleton structure of morphing nose cone for aerospace vehicle inspired by variable geometry mechanism of honeybee abdomen, Aerospace Science and Technology, 92, 2019. Crossref

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