Aerodynamic test and analysis of wrap-around fins at supersonic Mach numbers utilizing design of experiments

Swenson, Mark; Abate, Gregg; Whyte, Robert H.

doi:10.2514/6.1994-200

Cited by 4 publications

(3 citation statements)

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“…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%

See 1 more Smart Citation

Comparison of Flow field in the proximity of A Single Planar & Wrap-around Fin

Sharma¹,

Saini²,

Chaudhary³

et al. 2019

IJAAA

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Section: Discussionmentioning

confidence: 99%

“…For the validation of single wrap-around fin model, the predicted drag coefficient values were compared with the experimental counterparts (Abate & Hathaway, 1994;Abate & Winchenbach, 1991;Swenson, Abate & Whyte, 1994;Vitale et al, 1992;Wichenbach, Buff, Whyter, & Hathaway, 1986). See Figure 27.…”

Section: Verification and Validationmentioning

confidence: 99%

Comparison of Flow field in the proximity of A Single Planar & Wrap-around Fin

Sharma¹,

Saini²,

Chaudhary³

et al. 2019

IJAAA

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“…Aerodinamika olučastih krila detaljno je izučavana primenom savremenih numeričkih metoda ili ispitivanjem u aerotunelu pri različitim Mahovim brojevima [6], [7], [8] i [9]. Aerodinamički moment valjanja nastaje usled diferencijalnog otklona konzola stabilizatora u odnosu na uzdužnu osu rakete i asimetrije opstrujavanja koja je izazvana oblikom olučastih krila i javlja se i pri nultim vrednostima napadnog ugla (α) i ugla ugradnje krila (δ l ).…”

Section: Sl 5 -Ugaona Brzina Valjanjaunclassified

Influence of range extension on dynamic stability for artillery rockets with wrap around fins

Ćuk¹

2007

Vojnotehni?ki glasnik

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Vojnotehničkog instituta, BeogradRezime: U radu su prikazani efekti povećanja dometa artiljerijske rakete sa olučastim krilima na njenu dinamičku stabilnost. Totalni impuls raketnog motora, uvećan za 50% i let rakete kroz slojeve atmosfere sa malom gustinom vazduha povećavaju domet rakete za više od 75% od nominalnog dometa. Međutim, let rakete kroz razređeni vazduh proizvodi teškoće koje se odnose na dinamičku stabilnost. Male promene bočnog momenta indukovanog napadnim uglom i Magnusovog momenta mogu proizvesti nestabilnost kretanja i nedozvoljeni rast napadnog ugla. Određene su tolerancije bočnog momenta za osnovnu i poboljšanu varijantu rakete radi sprečavanja nestabilnog leta. Analiziran je, takođe, uticaj povećanja dometa na verovatna odstupanja rakete po dometu i pravcu. Ključne reči: nevođena raketa, putanja, dinamička stabilnost, rasturanje, olučasta krila. Summary:This paper presents the effects of the range extension of an artillery rocket with wrap around fins on its dynamic stability. The increased total impulse of the rocket engine for 50% and flight through the atmosphere layers with low air density extend the range for more than 75% of the nominal range. However, the flight of the unguided rocket through the rarefied air produces difficulties related to the dynamic stability. The small changes in the side moment which is induced by the angle of attack and Magnus moment of the improved rocket can produce instabilities in flight and increasement the angle of attack. The tolerances of the side moment were determined for both basic and improved type of the rocket in order to prevent instable flight. The influence of the range extension on the probable errors in range and cross-range was analyzed as well.

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Computational Flow Field Analysis around a Single Wrap-around Fin

et al. 2020

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A flow field aerodynamic analysis using Computational Fluid Dynamics (CFD) model of a single wrap around fin is performed at 0° angle of attack and its flow visualizations are presented in this paper for a subsonic to supersonic Mach range. A comparative study is performed by utilizing two WAF geometries aligned in opposite directions and with different edges (Sharpened and Blunt). The aerodynamic characterization has been conducted using a realizable κ-ϵ turbulence model utilizing a high-quality mesh to understand the nuances of the flow around the curved fin structure. The quantities of interest are the computed aerodynamic coefficients which have been validated with their precursors. By investigating the contours of the pressure coefficient and the relative Mach number, the flow phenomenon in the vicinity of the curved fin can be understood in a finer way.

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Aerodynamic test and analysis of wrap-around fins at supersonic Mach numbers utilizing design of experiments

Cited by 4 publications

References 0 publications

Comparison of Flow field in the proximity of A Single Planar & Wrap-around Fin

Comparison of Flow field in the proximity of A Single Planar & Wrap-around Fin

Influence of range extension on dynamic stability for artillery rockets with wrap around fins

Computational Flow Field Analysis around a Single Wrap-around Fin

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