Subsonic and transonic aerodynamics of a wraparound fin configuration

Winchenbach, G. L.; Buff, R.; Whyte, Robert H.; Hathaway, Wayne

doi:10.2514/3.20156

Cited by 26 publications

(11 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The wrap-around fin conforms to the cylindrical shape of the projectile while in the launch tube, allowing more efficient use of space. Thus, greater numbers of wrap-around fin projectiles can be stored in the same space as fixed-fin projectiles designed to deliver the same payload (Dahlke 1975;Winchenbach 1986). …”

Section: Introductionmentioning

confidence: 99%

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

Edge

1993

31st Aerospace Sciences Meeting

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

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

Edge

1993

31st Aerospace Sciences Meeting

View full text Add to dashboard Cite

“…Once again, the nonuniform Mach number profile at the fin plane suggests the presence of a curved shock of varying strength from the fin root to tip. The difference in the rolling moment for the pinched and blunt tip models suggest that the nonzero rolling moment is not only due to the vortex formation reported by Tilmann, et al [17] but the fin leading edge shape also plays an important role by dictating the leading edge shock structure, as reported by Winchenbach, et al [15], responsible for flow retardation away from the finbody junction. The difference in fluid dynamics for a pinched leading edge model and a blunt leading edge model is further illustrated in Figs.…”

Section: Static Pressure Profile Mach No Profilementioning

confidence: 63%

“…Rolling moment is positive at subsonic velocity (missile roll towards the concave side of the fin) and roll reversal was experienced at about Mach No 1.0. Winchenbach [15], et al conducted the free flight aeroballistics tests to obtain aerodynamic data over Mach number from 0.6 to 1.35 for a WAF configuration at atmospheric pressure. Results of their analysis indicated that dynamic instability exists above Mach No.…”

Section: Introductionmentioning

confidence: 99%

Anomalies in the Flow over Projectile with Wrap-around Fins

Krishna¹,

Surit²,

Kushari³

et al. 2009

DSJ

View full text Add to dashboard Cite

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.

show abstract

“…The computed Lift coefficients values from these models might not be useful. Abate 1991Swenson, M W 1994Whyte, 1986Vitale, R E, 1992 Present CFD However, such models are perfect for understanding the flow aerodynamics around the various fin geometries, and, useful for the prediction of Drag as well as Rolling moment coefficients at zero-degree angle of attack. The flow characteristic comparison has been done for both the planar as well as the wrap-around fin in the complete Mach number range of ~0.4M to 3.0M.…”

Section: Discussionmentioning

confidence: 99%