LIFT PERFORMANCE OF A TWIST MORPHING MAV WING

Authors

  • N.I. Ismail Faculty of Mechanical Engineering, Universiti Teknologi MARA, 13500 Permatang Pauh, Pulau Pinang, Malaysia
  • A.H. Zulkifli Faculty of Mechanical Engineering, Universiti Teknologi MARA, 13500 Permatang Pauh, Pulau Pinang, Malaysia
  • M. Hisyam Basri Faculty of Mechanical Engineering, Universiti Teknologi MARA, 13500 Permatang Pauh, Pulau Pinang, Malaysia
  • R.J. Talib Faculty of Mechanical Engineering, Universiti Teknologi MARA, 13500 Permatang Pauh, Pulau Pinang, Malaysia
  • H. Yusoff Faculty of Mechanical Engineering, Universiti Teknologi MARA, 13500 Permatang Pauh, Pulau Pinang, Malaysia

DOI:

https://doi.org/10.11113/jt.v75.5206

Keywords:

Micro air vehicle (MAV), fluid structure interaction, morphing wing, aerodynamics

Abstract

The manoeuvrability performance of a twist morphing MAV has been the main interest for the past researches. However, aerodynamic behaviour of a twist morphing wing is not fully explored due to limited MAV wing size, limited energy budgets, complicated morphing mechanism, and complex aerodynamic-wing structural interaction. Therefore, the effect of a twist morphing wing mobility on the lift distribution of MAV wing is still remained unknown. Thus, present work was carried out to compare the lift performance between a twist morphing wing with membrane and rigid MAV wing design. A quasi-static aeroelastic analysis by using the Ansys-Fluid Structure Interaction (FSI) method is utilized in current works to calculate the lift performance for each MAV wing design. Each MAV wing has identical wing dimension except for twist morphing wing where a 3N morphing force was imposed on the wing to produce the twist mobility. The lift results show that twist morphing wing able to produce (5% to 20%) higher lift magnitude compared to the membrane and rigid wing for every angle attack cases at pre-stall angle. However, twist morphing wing had slightly suffered from (at least 1°) earlier stall angle and produced almost similar maximum lift coefficient magnitude to the membrane wing 

 

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Published

2015-08-20

Issue

Vol. 75 No. 8: Advances In Aerospace & Automotive

Section

Science and Engineering

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Copyright of articles that appear in Jurnal Teknologi belongs exclusively to Penerbit Universiti Teknologi Malaysia (Penerbit UTM Press). This copyright covers the rights to reproduce the article, including reprints, electronic reproductions, or any other reproductions of similar nature.

How to Cite

LIFT PERFORMANCE OF A TWIST MORPHING MAV WING. (2015). Jurnal Teknologi, 75(8). https://doi.org/10.11113/jt.v75.5206