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Journal of Projectiles, Rockets, Missiles and Guidance >

2011 , Vol. 31 >Issue 4: 207 - 209

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.04.032

CORRELATION TECHNOLOGY

The Application of Transfinite Interpolation to Numerical Simulation of Control Surface Oscillating Deflection

  • DONG Linlin
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  • No. 91550 Unit, Liaoning Dalian 116023, China

Received date: 2010-10-10

  Online published: 2025-05-30

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Abstract

To study the response of aerodynamic force to the unsteady oscillation of control surface, an unsteady RANS solver and a deforming grid algorithm based on arc-length-based transfinite interpolation were applied to simulate the flap oscillation of NLR7301 two-element airfoil and the horizontal elevator's oscillation of a square section missile. The results show that the defor-ming grid algorithm can maintain grid orthogonality and smoothness of the original grid. The method in this paper could simulate the hysteresis loop of the aerodynamic characteristics caused by the unsteady pitching motion of the control surfaces.

Key words： control surface; oscillating deflection; trans-finite interpolation (TFI); hysteresis

Cite this article

DONG Linlin . The Application of Transfinite Interpolation to Numerical Simulation of Control Surface Oscillating Deflection[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011 , 31(4) : 207 -209 . DOI: 10.15892/j.cnki.djzdxb.2011.04.032

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