Analysis of missile configurations with wrap-around fins using computational fluid dynamics

Abate, Gregg; Cook, Theresa

doi:10.2514/6.1993-3631

Cited by 15 publications

(12 citation statements)

References 2 publications

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“…Previous CFD studies [9][10][11][12][13] of missile configurations with WAF have shown general agreement with experimental data of roll reversal, but always lacked accuracy in roll moment and side moment determination. Edge [11] considered both inviscid as well as viscous flows and calculated the roll moment using a three-dimensional full Navier-Strokes code.…”

Section: Introductionmentioning

confidence: 97%

“…Edge [11] considered both inviscid as well as viscous flows and calculated the roll moment using a three-dimensional full Navier-Strokes code. Abate and Cook [12] calculated the roll moment of WAFs attached to an infinitely long cylinder using Euler code. They pointed out that the accuracy of CFD greatly depends on the configuration modelled.…”

Section: Introductionmentioning

confidence: 99%

“…So they considered fin thickness to be the critical parameter in WAF aerodynamics. They explained the roll moment reversal with the concept of converging diverging nozzle [12]. Paek [13], et al further showed that the edge and tip shapes too have a great significance in the roll moment of WAF.…”

Section: Introductionmentioning

confidence: 99%

“…However, the computational simulation [16] and experimental studies [17] on a single WAF by Tilmann [16,17], et al suggest the vortex formation at the fin/body juncture at the convex side of the fin can be the cause of roll reversal. Abate and Cook [12] explained roll reversal phenomenon as converging-diverging analogy. However, if it would have been the reason, then roll reversal would have been reported at Mach No.…”

Section: Introductionmentioning

confidence: 99%

“…Furthermore, the roll reversal Mach number, reported by various researchers had never been consistent. Few previous computational works were been done while neglecting some important [12], Paek [13], et al and Edge [11] are computational work. As shown in Table 1, no particular cross-over point has been uniformly observed.…”

Section: Introductionmentioning

confidence: 99%

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Anomalies in the Flow over Projectile with Wrap-around Fins

Krishna¹,

Surit²,

Kushari³

et al. 2009

DSJ

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This paper presents the results of a numerical study to understand the flow field over a projectile with wraparound fins. This investigation is performed in order to determine aerodynamic coefficients for the missile model for varying Mach number from 1.2 to 2.5. The roll moment coefficients were computed from the flow field solution and compared with other computational models and experimental works. The results show a reversal of the rolling moment in a Mach number from 1.2 to 1.4. While generating Mach number profile along missile body, a transition from subsonic to supersonic flow was notably found just before the fin-tip in the Mach number range from 1.2 to 1.4. This transition from subsonic to supersonic just before the fin seems to be the main cause for the roll reversal, which makes the flow inside the fin passage behave differently. Furthermore, it was seen that most of the effect was confined towards the leading edge of the fins.

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Section: Introductionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Anomalies in the Flow over Projectile with Wrap-around Fins

Krishna¹,

Surit²,

Kushari³

et al. 2009

DSJ

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The simulation of single wraparound fin on a semi-cylindrical missile body

Sharma

Kumar

2020

AEAT

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Purpose The purpose of this paper is to establish a freestream computational fluid dynamics (CFD) model of a three-dimensional non-spinning semi-cylindrical missile model with a single wrap around fin in Mach 2.70-3.00M range and 0° angle of attack, and ultimately establishing itself for future research study. Design/methodology/approach In this study, the behaviour of flow around the fin was investigated using a κ-ϵ turbulence model of second-order of discretization. This was done using a highly structured mesh. Additionally, an inviscid CFD simulation involving the same boundary conditions have also been carried out for comparison. Findings The obtained values of aerodynamic coefficients and pressure contours visualizations are compared against their experimental and computational counterparts. A typical missile aerodynamic characteristic trend can be seen in the current CFD. Practical implications The predicted values of the aerodynamic coefficients of this single fin model have also been compared to those of the full missile body comprising of four fins from the previous research studies, and a similar aerodynamic trend can be seen. Originality/value This study explores the possibility of the use of turbulence modelling in a single fin model of a missile and provides a basic computational model for further understanding the flow behaviour near the fin.

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Numerical investigation of aberrant aerodynamic behavior of wrap-around fins in collation with planar fins

Umar¹,

Mian²

2015

2015 12th International Bhurban Conference on Applied Sciences and Technology (IBCAST)

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The anomalistic aerodynamic behavior of wrap around fins has kept the researchers engrossed in devising new design methods and analysis techniques. Rolling moment at zero incidence angle, induced forces and moments due to fin curvature, roll reversal phenomenon, static side moment and Magnus side moment are the main aggravations that make their aerodynamics more complex when compared with the planar fins. The present research effort provides a deep insight and explanation for this uncertain aerodynamics associated with wrap-around fins. At first, simulations of flow around isolated planar fin and curved fin has been performed to identify the effect of curvature. The results indicate a pressure loading for the curved fin at zero incidence angle, which was more confined towards the leading edge. Both curved and flat fins showed symmetric pressure distribution about mid chord on top and bottom surfaces. As a result, no side force was observed for isolated fins. Pressure loadings have distinct divisions for both the planar and curved fins that are similar in appearance to Mach lines. Subsequently, the effect of wall and the support hinges have been studied for wrap-around fins. Due to wall boundary the pressure distribution becomes asymmetric, which originates a side force. The presence of the support hinges creates shocks patterns at the bottom surface and generates unbalanced pressure loading. The predicted aerodynamic load for the wrap around fins is then used to perform static computational aeroelastic analysis to obtain true structural deformations. The results highlights the fact that the uneven structural displacements give rise to out of the plane forces that effects the aerodynamics and flight performance of systems with wrap around fins.

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Analysis of missile configurations with wrap-around fins using computational fluid dynamics

Abstract: AbsuactBackground

Cited by 15 publications

References 2 publications

Anomalies in the Flow over Projectile with Wrap-around Fins

Anomalies in the Flow over Projectile with Wrap-around Fins

The simulation of single wraparound fin on a semi-cylindrical missile body

Numerical investigation of aberrant aerodynamic behavior of wrap-around fins in collation with planar fins

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