DEVELOPMENT OF A DYNAMIC WIND TUNNEL RIG FOR AIRCRAFT PURE PITCHING MOTION

Authors

  • Shuhaimi Mansor Department of Aeronautics and Automotive Faculty of Mechanical Engineering Universiti Teknologi Malaysia 81310 Johor Bahru, Johor
  • Iskandar Shah Ishak Department of Aeronautics and Automotive Faculty of Mechanical Engineering Universiti Teknologi Malaysia 81310 Johor Bahru, Johor
  • Ong Meng Wei Department of Aeronautics and Automotive Faculty of Mechanical Engineering Universiti Teknologi Malaysia 81310 Johor Bahru, Johor
  • Istas Fahrurazi Department of Aeronautics and Automotive Faculty of Mechanical Engineering Universiti Teknologi Malaysia 81310 Johor Bahru, Johor

Keywords:

Keywords

Abstract

This paper presents the design, fabrication and testing of a
dynamic wind tunnel test rig that is used in conjunction with
aircraft dynamics theory in estimating aerodynamics stability
derivatives. The value of ce; and Cmq + Cma can be obtained from
free oscillation theory ofpure pitching motion. The rig comprises a
scale down 1:30 full model of two-seater light aircraft,
accelerometer, charge amplifier, AID converter and IBM-PC. The
result of the study has shown that the test rig is capable of
predicting the derivatives. The effect of Reynold's number to the
dynamics testing can be considered small as in dynamic testing,
where the rate of change was measured rather than the absolute
value. Finally, the rig can be used as part of the experimental
testing in flight dynamics for aircraft design.

References

Nelson, R.c., 1989, Flight Stability and Automatic Control, MacGrawHill Book Company, New York.

McLean, D., 1990, Automatic Flight Control Systems, Prentice Hall International, London.

Pope, A., 1965, High Speed Wind Tunnel Testing, John Wiley and Sons, New York.

Ong Ming Wei, 1998, The Design and Development of A Digital

Computer Interface f or the Dynamic Wind Tunnel Test Rig, Faculty of Mechanical Eng ., UTM.

Iskandar Shah Ishak, 1996, Development of A Wind Tunnel Test Rig for Pure Pitching Motion, Faculty of Mechanical Eng ., UTM.

Shingkey, lE., and Mischkes C.R., 1989, Mechanical Engineering Design, McGraw Hill Book Company, US.

Soltani, M.R. , 1988, Experimental Measurement on an Oscillating 70 Degree Delta Wing in Subsonic Flow, AIAA 6th Applied Aerodynamic Conference, United States.

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Published

2018-05-16

How to Cite

Mansor, S., Ishak, I. S., Meng Wei, O., & Fahrurazi, I. (2018). DEVELOPMENT OF A DYNAMIC WIND TUNNEL RIG FOR AIRCRAFT PURE PITCHING MOTION. Jurnal Mekanikal, 10(2). Retrieved from https://jurnalmekanikal.utm.my/index.php/jurnalmekanikal/article/view/272

Issue

Issue 10: December 2000

Section

Mechanical

License

Copyright of articles that appear in Jurnal Mekanikal 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.

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