News

 Statistics

Number of Journals34
Number of Issues1,306
Number of Articles9,428
Article View9,191,233
PDF Download5,622,141
yazdani, K., Naderi, A. (2020). The Effect of the Geometric Parameters of the Fin on Aerodynamic Performance of Missile.. Electronic and Cyber Defense, 8(2), 141-151.
khashayar yazdani; Aliasghar Naderi. "The Effect of the Geometric Parameters of the Fin on Aerodynamic Performance of Missile.". Electronic and Cyber Defense, 8, 2, 2020, 141-151.
yazdani, K., Naderi, A. (2020). 'The Effect of the Geometric Parameters of the Fin on Aerodynamic Performance of Missile.', Electronic and Cyber Defense, 8(2), pp. 141-151.
yazdani, K., Naderi, A. The Effect of the Geometric Parameters of the Fin on Aerodynamic Performance of Missile.. Electronic and Cyber Defense, 2020; 8(2): 141-151.

The Effect of the Geometric Parameters of the Fin on Aerodynamic Performance of Missile.

مکانیک سیالات و آیرودینامیک
Article 11, Volume 8, Issue 2 - Serial Number 24, June 2020, Pages 141-151    PDF (1.24 M)
Document Type: Original Article
Authors
khashayar yazdani1; Aliasghar Naderi2
1Department of mechanical engineering, Gilan university
2Department of Mechanical engineering, Imam ali university
Receive Date: 30 September 2019,  Accept Date: 23 June 2020 
Abstract
In the aerodynamic design of missiles, it is necessary to consider a wide design space. The complexity of a design space depends on the number of input variables. Missile diameter, nozzle, body length, the number of rows of fin, the number of fins for each row, the size and shape of each ffin, and their cross-section can be provided as examples of design variables. In this study, the aerodynamic characteristics of drag force , lift force, rotational torque, maneuverability, lift-drag force ratio as well as compressive force at Mach numbers and different attack angles were investigated. The results showed that aerodynamic coefficients increased with the addition of a fin in front of the missile. It is also observed that the stability of the missile improves when the fin is near the end of the missile but the ratio of lift to drag and maneuverability is reduced. It was also found that by increasing the length and height of the fin lifting force to the drag force, vertical force and the stability of missile increases. Also, it was observed that lift-drag force ratio increases with the increase in the number of fin rows.
Keywords
Aerodynamic; Fin; Attack angle; Mach number
References
  1. Akgül, A., Akargün, H. Y., Atak, B., Çetiner, A. E., and Göker, O. “Numerical investigation of NASA tandem control missile and experimental comparison”, Sci. Tech. Rev. Vol. 62, No. 1, pp.3-9, 2012.##
  2. Yang, Y. R., Jung, S. K., Cho, T. H., and Myong, R. S. “Aerodynamic shape optimization system of a canard-controlled missile using trajectory-dependent aerodynamic coefficients”. J Spacecraft Rockets.  Vol. 49, No. 2, pp. 243-249, 2012.##
  3. Tanrikulu, O., and Ercan, V. “Optimal external configuration design of unguided missiles”. J Spacecraft Rockets. Vol. 35, No. 3, pp. 312-316. 1998.##
  4. Tanil, C., Platin, B., and Mahmutyazicioglu, G. “External configuration optimization of missiles in conceptual design”. In AIAA atmospheric flight mechanics conference, p. 5719, 2009.##
  5. Graves, E. B., & Fournier, R. H. “Stability and control characteristics at Mach numbers from 0.20 to 4.63 of a cruciform air-to-air missile with triangular canard controls and a trapezoidal wing”. 1974.##
  6. Yin, B., Xu, D., An, Y. R., and Chen, Y. S. “Aerodynamic optimization of 3D wing based on iSIGHT”. Appl Math Mech-Engl, Vol. 29, No. 2, pp.603-610, 2008.##
  7. Yue, C. G., Chang, X. L., Yang, S. J., and Zhang, Y. H. “Numerical Simulation on Aerodynamic Characteristic of an Air-to-Air Missile”. International Workshop on Computer Science for Environmental Engineering and EcoInformatics, Springer, Berlin, Heidelberg, 2011.##
  8. Sigal, A. “Comparative Aerodynamic Analysis Of A Missile With An Eight-Fin Tail”. 23rd International Symposium On Ballistics Tarragona (pp.16-20), Spain, 2007.##
  9. Guide, A. F. U. Release 14.0, ANSYS. Inc., USA, November, 2011.##
Statistics
Article View: 802
PDF Download: 514