Computation of the roll moment coefficient for a projectile with wrap-around fins

Edge, Harris L.

doi:10.2514/6.1993-499

Cited by 8 publications

(13 citation statements)

References 5 publications

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“…They also showed that Euler equations can give comparably accurate solutions when computing the roll moment of WAF configuration. Their comparison with Edge [11] showed that the fin tip, when pinched, shows complete agreement with the experimental data.…”

Section: Introductionmentioning

confidence: 55%

“…The standard TTCP configuration has fins with symmetric leading and trailing edge bevels, with a difference of 45°e xists between the root and tip chord cross section. Previous computational studies [11,13] were done with blunt leading and trailing edges. In the present study, two configurations have been developed, one with blunt leading edge and the other with a pinched leading edge.…”

Section: Numerical Formulationmentioning

confidence: 99%

“…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.…”

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: 55%

Section: Numerical Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 97%

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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