Numerical simulation of the flow around a projectile passing through a shock wave

Watanabe, Rikio; Fujii, Kozo; Higashino, Fumio

doi:10.2514/6.1995-1790

Cited by 10 publications

(13 citation statements)

References 5 publications

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“…This is probably due to a weakened blast wave owing to the attenuation of the blast wave to an extent where the pressure jump across the wave is smaller than that needed to create a drastic fluctuation in the drag characteristics ofthe projectile. This is in contrast with the results of Watanabe et al [3], where the blast wave maintains a constant strength throughout the overtaking process. In real situations as described here, the blast wave strength is diminishing rapidly and hence, it alters the flow conditions behind the blast wave.…”

Section: Projectiie Overtaking Processcontrasting

confidence: 99%

“…Although the effect of the viscosity on the projectile aerodynamic characteristics is not significant, the viscosity greatly affects the unsteady flow structures around the projectile. T HE UNSTEADY flowfields induced by the projectile when it is launched from a barrel attracted the attention of many researchers because it involves various complicated fluid dynamic processes associated with its motion [1][2][3][4][5][6][7][8][9]. The primary flow disturbances that make the flowfield quite unsteady and complex are the flow interfaces in the primary blast wave [10][11][12][13] and their interactions [14].…”

Section: Doi: 102514/1a32466mentioning

confidence: 99%

“…Watanabe et al [3] studied the fluid dynamics associated with the projectile overtaking problem. They used the one-dimensional (1-D) theory to analyze various overtaking criteria.…”

Section: Doi: 102514/1a32466mentioning

confidence: 99%

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Launch Dynamics of Supersonic Projectiles

Muthukumaran

Rajesh

Kim

2013

Journal of Spacecraft and Rockets

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The aerodynamics of projectiles launched from barrels of various devices is quite complicated due to their interactions with the unsteady flowfield around them, A compntational study using a moving grid method is performed here to analyze various fluid dynamic phenomena in the near field of a gun, such as the projectile-shock wave interactions and interactions between the flow structures and the aerodynamic characteristics ofthe projectile when it passes throngh various flow interfaces. Cylindrical and conical projectiles have been employed to study such interactions and the fluid dynamics of the flowflelds. The aerodynamic characteristics of the projectile are hardly affected by the projectile configuration dnring the process of the projectile overtaking the primary blast wave for small Mach numbers. However, it is noticed that the projectile configurations do affect the unsteady flow structures before overtaking and hence, the unsteady drag coeflicient for the conical projectile shows considerable variation from that of the cylindrical projectile. The projectile aerodynamic characteristics during the interaction with the secondary shock wave are also analyzed in detail. It is observed that the change in the characteristics of the secondary shock wave during the interaction is fundamentally diflerent for different projectile configurations. Both inviscid and viscous simulations were carried out to study the projectile aerodynamics and the fluid dynamics. Although the effect of the viscosity on the projectile aerodynamic characteristics is not significant, the viscosity greatly affects the unsteady flow structures around the projectile. NomenclatureSubscripts P S projected frontal area of the projectiles speed of sound, m/s coeflicient of drag drag force, N Mach number projectile Mach number relative to still air projectile Mach number relative to flow behind the moving shock wave shock wave Mach number at the launch tube exit. assumed parameter pressure, N/mt ime, ms velocity, m/s density, kg/mr atio of specific heats projectile shock wave = downstream and upstream of the moving shock wave

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Section: Projectiie Overtaking Processcontrasting

confidence: 99%

Section: Doi: 102514/1a32466mentioning

confidence: 99%

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Launch Dynamics of Supersonic Projectiles

Muthukumaran

Rajesh

Kim

2013

Journal of Spacecraft and Rockets

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“…There have been computational studies (Watanabe, Fujii & Higashino 1995;Jiang, Takayama & Skews 1998;Jiang 2003;Ahmadikia & Shirani 2005;Rajesh et al 2007;Rajesh, Kim & Setoguchi 2008;Muthukumaran, Rajesh & Kim 2013) to address the fundamental fluid flow interactions in the near field of a launch tube, and a reasonable understanding of various types of flow interactions has been acquired as briefly outlined below.…”

Section: Introductionmentioning

confidence: 99%

Flow interactions on supersonic projectiles in transitional ballistic regimes

et al. 2020

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“…These interactions affect the aerodynamic characteristics drastically. The unsteady flow-field of a projectile launch has been studied by many investigators [7][8][9][10][11] . Chand and Panda 12 studied the projectile trajectory using simplified point mass approach which considered only the drag force and the gravity force.…”

Section: Introductionmentioning

confidence: 99%

Flow Around a Conical Nose with Rounded Tail Projectile for Subsonic, Transonic, and Supersonic Flow Regimes : A Numerical Study

Kumar

Panda

Biswal

et al. 2014

DSJ

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Flow around a conical nose with rounded tail projectile has been studied numerically for subsonic, transonic and supersonic flow regimes. The conic angle of the projectile is 10°. The inflow Mach numbers are 0.5, 0.9, and 1.5. Axisymmetric Euler's equations are solved for predicting the drag coefficient. It has been observed that even for a subsonic flow regime, the Mach number distribution is not uniform owing to the non-symmetric shape of the projectile. The predicted drag coefficients for subsonic, transonic, and supersonic cases are 0.018, 0.089, and 0.395, respectively. It was observed that rounded tail is a better option than boat tail so far drag force is concerned.

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Numerical simulation of the flow around a projectile passing through a shock wave

Cited by 10 publications

References 5 publications

Launch Dynamics of Supersonic Projectiles

Launch Dynamics of Supersonic Projectiles

Flow interactions on supersonic projectiles in transitional ballistic regimes

Flow Around a Conical Nose with Rounded Tail Projectile for Subsonic, Transonic, and Supersonic Flow Regimes : A Numerical Study

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