Research on Aerodynamic Characteristics of Lateral Jet Control Technology

Abstract:

This paper takes N-S equation as the basic control equation, selects turbulence model, and adopts the sliding mesh technology to conduct numerical simulation for the interference of missile jet flow and inflow on the flow field in different flow conditions. The results indicate that: the lift coefficient, drag coefficient and pressure center coefficient of missile body change with the changes of flowMach number and attack angle. The lift coefficient increases with the increase of Mach number in subsonic speed, decreases with the increase of Mach number in supersonic speed, and reaches a maximum value with the increase of Mach number in transonic speed. The change rule of drag coefficient and pressure center coefficient is the same as that of lift coefficient. That is, they increase with the increase of Mach number in subsonic speed, and decrease with the increase of Mach number in supersonic speed.

• Periodical: Advanced Materials Research (Volume 709)
• Pages: 253-256
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.709.253
• Online since: June 2013
• Authors: Xing Xu, Jun Hu
• Keywords: Aerodynamic Characteristics, Lateral Jet, Sliding Mesh

References

[1] Hu Jun, Lei Juanmian, Wu Jiasheng. Research and Application of Lateral Jet Control in Missile Technology [J]. Journal of Projectiles, Rockets, Missiles and Guidance, Vol. 22 (3).(In Chinese)

[2] Wu Xiaoping et al. Numerical Simulation Includes Flow Field around Jet Missiles. Journal of Propulsion Technology, 1998,19 (3): 57 60.(In Chinese)

[3] Julius Brandeis, Jacob Gill. Experiment investigation of supersonic and hypersonic jet interaction on missile configurations[J]. Journal of Spacecraft and Rockets,1998,35(3):296~ 302.

DOI: 10.2514/2.3354

[4] Graham M J.A numerical investigation of supersonic jet interaction for finned bodies[R]. AIAA Paper20000768,2000.

[5] Batchelor G K. An introduction to fluid dynamics[M]. UK: Cambridge University Press, 1967: 555-557.