Numerical Simulation on Supersonic Aerodynamic Interference for Rigid and Flexible Parachutes

Xue, Xiaopeng; Koyama, Hiroto; Nakamura, Yu

doi:10.2514/6.2012-3269

Cited by 4 publications

(4 citation statements)

References 6 publications

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“…In the previous numerical study for a rigid parachute, 18) the turbulence model was not used, the results of which were in good agreement with experimental data obtained at ISAS/JAXA. The flow calculation code for the rigid case is employed here.…”

Section: Computational Methods 321 Flow Calculationsupporting

confidence: 76%

“…The configuration of this parachute system is shown in Fig. 1, which is basically the same as that of the rigid parachute model employed in the previous research, 18) except the thickness of the canopy here is zero in a geometrical sense.…”

Section: Parachute Modelmentioning

confidence: 58%

“…10), 9) since under the condition of these values, complicated aerodynamic interference was observed in the case of the rigid parachute system in our previous research. 18) Therefore, it seems to be worth examining whether such phenomena will also occur in the case of the flexible parachute system. Table 1) in this study; the yellow region refers to the capsule body, and the red region the canopy surface.…”

Section: Parachute Modelmentioning

confidence: 99%

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Numerical Simulation of a Three-Dimensional Flexible Parachute System under Supersonic Conditions

Xue

Nakamura

2013

AEROSPACE TECHNOLOGY JAPAN

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In the present study, the supersonic flow over a three-dimensional flexible parachute system is numerically simulated using a simple "immersed boundary method" together with the weak fluid-structure coupling scheme. The parachute system employed here consists of a capsule and a canopy. The mass-spring-damper model is applied to solve the structural dynamics of the flexible parachute system. The objective of this study is to analyze the effects of aerodynamic interaction such as wake/shock interaction on the dynamics of the canopy behavior, and clarify the performance of the flexible parachute system in terms of Mach number, the ratio of a capsule to a canopy diameter, and the trailing distance between the capsule and canopy. As a result, it is found that there are two key factors for the dynamics of the parachute system: one is the unsteady change in canopy shape and the other the aerodynamic interference between the capsule wake and the canopy shock. As the trailing distance increases reasonably, the area oscillation of the canopy shape is observed. However, by reducing the canopy size in the certain smaller trailing distance case, the canopy deformation is improved. Moreover, it is found that the free stream Mach number has a big impact on the canopy behavior in the smaller Mach number case, where the canopy undergoes smaller deformation, leading to a larger drag coefficient.

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Section: Computational Methods 321 Flow Calculationsupporting

confidence: 76%

Section: Parachute Modelmentioning

confidence: 58%

Section: Parachute Modelmentioning

confidence: 99%

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Numerical Simulation of a Three-Dimensional Flexible Parachute System under Supersonic Conditions

Xue

Nakamura

2013

AEROSPACE TECHNOLOGY JAPAN

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“…Barnhardt et al [11] used the detached-eddy simulation (DES) method to investigate the influence of the time-varying deficit in the capsule wake interacting with the bow shock on the canopy. In recent years, some researchers conducted many wind tunnel experiments and numerical simulations on the parachute system [12][13][14][15][16][17] . It can be found that in the supersonic flow field, the fluid inside and outside the parachute system is characterized by significant turbulent flow.…”

Section: Introductionmentioning

confidence: 99%

A study of a supersonic capsule/rigid disk-gap-band parachute system using large-eddy simulation

Gong

2021

Appl. Math. Mech.-Engl. Ed.

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The aerodynamic performances and flow features of the capsule/rigid disk-gap-band (DGB) parachute system from the Mach number 1.8 to 2.2 are studied. We use the adaptive mesh refinement (AMR), the hybrid tuned center-difference and weighted essentially non-oscillatory (TCD-WENO) scheme, and the large-eddy simulation (LES) with the stretched-vortex subgrid model. The simulations reproduce complex interaction of the flow structures, including turbulent wakes and bow shocks, as well as bow shocks and expansion waves. The results show that the calculated aerodynamic drag coefficient agrees well with the previou simulation. Both the aerodynamic drag coefficient and the aerodynamic drag oscillation of the parachute system decrease with the increase of the initial Mach number of the fluid. It is found that the position and angle of the bow shock ahead of the canopy change as the Mach number increases, which makes the flow inside the canopy and the turbulent wake behind the canopy more complex and unstable.

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Experimental Investigations on Flexible Parachutes in Supersonic Flow

Taguchi¹,

Semba²,

Okada³

et al. 2015

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCE

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Numerical Simulation on Supersonic Aerodynamic Interference for Rigid and Flexible Parachutes

Cited by 4 publications

References 6 publications

Numerical Simulation of a Three-Dimensional Flexible Parachute System under Supersonic Conditions

Numerical Simulation of a Three-Dimensional Flexible Parachute System under Supersonic Conditions

A study of a supersonic capsule/rigid disk-gap-band parachute system using large-eddy simulation

Experimental Investigations on Flexible Parachutes in Supersonic Flow

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