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Numerical Investigation of Aerodynamic Performance of Planar/grid Stabilizer wings at Downstream Control Surface in Transonic Flow Regime

Document Type : Original Article

Authors

1 Department of Mechanical Engineering, Shahid Rajaee teacher training University, Tehran

2 Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

Abstract

In multi-stage Missiles, stabilizer wings are responsible for stabilizing the Missile. The control fins located upstream of the stabilizer wings affect the flow by spinning, which influences stability as well as control. One method for resolving this problem is to design stabilizer wings with less affectability against the upstream flow. The present paper deals with this issue by considering multiple planar fins and grid fins. Once validation is performed, after selecting the appropriate turbulence model and choosing the planar and grid fins, the appropriate Missile model is established; then, on a model with speeds of 0.6, 0.7, and 0.8 Mach, at attack angles of 0, 2, 4, and 6 degrees, and with control fins, variation at angles of 0, 1, 3, and 6 degrees, the aerodynamic coefficients as well as the effects of the upstream stabilizer wings are investigated in pitch and roll modes at an appropriate trim angle . The obtained results indicated that the use of grid fin downstream of the control surfaces would be less affected due to its physical nature; thus, the lower capacity of the control surface would be used for control during the flight, which would significantly facilitate the process of designing.

Keywords

Main Subjects

Article Title [Persian]

Numerical Investigation of Aerodynamic Performance of Planar/grid Stabilizer wings at Downstream Control Surface in Transonic Flow Regime

Authors [Persian]

  • Mahdi Miralam 1
  • Amir Rahni 2

1 Department of Mechanical Engineering, Shahid Rajaee teacher training University, Tehran

2 Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

Abstract [Persian]

In multi-stage Missiles, stabilizer wings are responsible for stabilizing the Missile. The control fins located upstream of the stabilizer wings affect the flow by spinning, which influences stability as well as control. One method for resolving this problem is to design stabilizer wings with less affectability against the upstream flow. The present paper deals with this issue by considering multiple planar fins and grid fins. Once validation is performed, after selecting the appropriate turbulence model and choosing the planar and grid fins, the appropriate Missile model is established; then, on a model with speeds of 0.6, 0.7, and 0.8 Mach, at attack angles of 0, 2, 4, and 6 degrees, and with control fins, variation at angles of 0, 1, 3, and 6 degrees, the aerodynamic coefficients as well as the effects of the upstream stabilizer wings are investigated in pitch and roll modes at an appropriate trim angle . The obtained results indicated that the use of grid fin downstream of the control surfaces would be less affected due to its physical nature; thus, the lower capacity of the control surface would be used for control during the flight, which would significantly facilitate the process of designing.

Keywords [Persian]

  • Grid fin
  • Inductive roll
  • Aerodynamic coefficient
  • Static margin
  • Pitch
References
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[19] Cai, J., “Numerical study on choked flow over grid-fin configurations”, Journal of Spacecraft and Rockets 46(5):949-956, (2009).
 
[20] Theerthamalai, P. and N. Balakrishnan, “Effect of geometric parameters on the aerodynamic characteristics of grid-fin cells at supersonic speeds”, 45th AIAA aerospace sciences meeting and exhibit, Reno, USA, (2007, January).
 
[21] Abate, G.L., R.P. Duckerschein, and W. Hathaway, “Subsonic/transonic free-flight tests of a generic missile with grid fins”, 38th AIAA aerospace sciences meeting and exhibit, Reno, USA, (2000, January).
Journal of Aerospace Science and Technology
Volume 15, Issue 2
October 2022
Pages 119-134
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