Navier-Stokes computations for a reacting, M864 base bleed projectile

Nietubicz, Charles J.; Gibeling, H. J.

doi:10.2514/6.1993-504

Cited by 16 publications

(6 citation statements)

References 16 publications

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“…Computations for the reacting M864 base bleed projectile provided results for the effect of temperature on the base region standoff distance that were not fully consistent with previous results of Nietubicz [10], which modeled the combustion process as a finite-rate reacting gas mixture. However, there are significant differences in the two approaches with respect to the combustion model, base bleed mass rate, numerical scheme, and turbulence model.…”

Section: Discussioncontrasting

confidence: 63%

“…An initial numerical investigation by Nietubicz and Gibeling [10] modeled the solid propellant combustion using the approach developed by Giebling and Buggeln [11]. This study [10] modeled the combustion as injectant gas mixtures of H 2 and H 2 /CO for a base bleed ratio of I = 0.0022.…”

Section: Subsonic and Supersonic Flow Past M864 Projectilementioning

confidence: 99%

“…This study [10] modeled the combustion as injectant gas mixtures of H 2 and H 2 /CO for a base bleed ratio of I = 0.0022. These combustion results were compared to results for hot air bleed and zero bleed conditions.…”

Section: Subsonic and Supersonic Flow Past M864 Projectilementioning

confidence: 99%

See 2 more Smart Citations

A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies

Catalano¹,

Sturek²

2001

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Section: Discussioncontrasting

confidence: 63%

Section: Subsonic and Supersonic Flow Past M864 Projectilementioning

confidence: 99%

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A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies

Catalano¹,

Sturek²

2001

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“…Having analyzed a reacting M864-base bleed projectile using Navier-Stokes computations in 1995, Nietubicz and Gibeling investigated the impact of the thrust force on velocity vectors in the wake area at Mach numbers of less than 1 to about 3, and eventually predicted the missile trajectory accurately [1]. Silton used Navier-Stokes computations for a spinning projectile from subsonic to supersonic speeds in di erent angles of attack in order to anticipate the in uence of whirling on the uid ow [2].…”

Section: Introductionmentioning

confidence: 99%

The Aerodynamic and Dynamic Analysis ofThree Common 4.5mm Caliber Pellets in a Transonic Flow

Rafeie¹,

Teymourtash²

2016

Scientia Iranica

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Abstract. In this paper, a numerical solution of the Navier-Stokes equations is considered using the Jameson method in the transonic ow regime over three air gun pellets. The considered pellets have the same caliber of 4.5 mm, but di erent nose shapes; they are axisymmetric projectiles of three basic types, namely wadcutter, sharp pointed, and roundnose. After these pellets have been modeled geometrically, the Navier-Stokes equations as the governing equations of the ow eld around the pellets are solved. Computed aerodynamic results have been used in order to analyze the trajectories of the projectiles, dynamically. The variation of the drag coe cient by Mach number of the free stream ow, which is a key point for the dynamic analysis of the projectile motion, has been obtained. The dynamic analysis of the motion of pellets precisely describes the trajectory and how the velocity of the pellet and the altitude slump with time and location. Relying on these analyses, from both aerodynamic and dynamic points of view, the round-nose pellet in a variable range of Mach numbers shows the best aerodynamic and dynamic behaviors in comparison with other pellets.

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“…RANS calculations were also employed for investigating different means of dragreduction, such as the effects of base bleed (see, e.g., Danberg & Nietubicz, 1992;Sahu & Heavey, 1995) and base burning (Nietubicz & Gibeling, 1993). The simulations showed a correct trend for the drag reduction when compared with experimental results but, in some cases, even global flow field characteristics such as the centerline velocity were not in good agreement with experiments.…”

Section: Turbulence Modellingmentioning

confidence: 99%

Simulation of Supersonic Base Flows: Numerical Investigations Using DNS, LES, and URANS

Fasel¹,

Sandberg²

2006

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Public Reporting Burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comment regarding this burden estimate or any other aspect of this collection of information, including suggesstions for reducing this burden, Simulation of Supersonic Base Flows: Numerical Investigations Using DNS, LES, and URANS Report Title ABSTRACTTransitional and turbulent supersonic axisymmetric wakes were investigated by conducting various numerical experiments. The main objective was to identify hydrodynamic instability mechanisms in the flow at Mach number M = 2.46 for several Reynolds numbers, and relating these to coherent structures that are found from various visualization techniques. The premise for this approach is the assumption that flow instabilities lead to the formation of coherent structures. The effect of these structures on the mean flow is of particular interest, as they strongly affect the base drag. Three high-order accurate compressible codes were developed in cylindrical coordinates for this research: A spatial Navier-Stokes (N-S) code to conduct Direct Numerical Simulations (DNS), a linearized N-S code for linear stability investigations using two-dimensional basic states, and a temporal N-S code for performing local stability analyses. The ability of numerical simulations to deliberately exclude physical effects is exploited. This includes intentionally eliminating certain azimuthal/helical modes by employing DNS for various circumferential domain-sizes. With this approach, the impact of structures associated with certain modes on the global wake-behavior can be scrutinized. It is concluded that azimuthal modes with low wavenumbers are responsible for a flat mean base-pressure distribution and that k=2 and k=4 are the dominant modes in the trailing wake, producing a four-lobe wake pattern. Complementary spatial and temporal calculations are carried out to investigate whether instabilities are of local or global nature. Circumstatial evidence is presented that absolutely unstable global modes within the recirculation region coexist with convectively unstable shear-layer modes. The flow is found to be absolutely unstable with respect to modes k>0 for Re_D > 5,000 and with respect to the axisymmetric mode for Re_D>100,000. Furthermore, it is investigated whether flow control measures designed to weaken the naturally most significant modes can decrease the base drag. Finally, the novel Flow Simulation Methodology (FSM), using state-of-the-art turbulence closures, was shown to reproduce DNS results at a fraction of the computational cost.

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Navier-Stokes computations for a reacting, M864 base bleed projectile

Cited by 16 publications

References 16 publications

A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies

A Numerical Investigation of Subsonic and Supersonic Flow Around Axisymmetric Bodies

The Aerodynamic and Dynamic Analysis ofThree Common 4.5mm Caliber Pellets in a Transonic Flow

Simulation of Supersonic Base Flows: Numerical Investigations Using DNS, LES, and URANS

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