Effects of Aircraft Tail Configurations on Sensitivity to Yaw Disturbances


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A wind tunnel test was conducted to compare the characteristics of low speed stability and control for aircraft with conventional tail and V-tail configurations. Comparison was made in terms of static directional stability at selected test speed of 40 m/s, which corresponds to Reynolds number of 0.1622 x 106 based on the chord. Three types of simplified tail-only model were tested in Universiti Teknologi Malaysia's Low Speed Wind Tunnel (UTM-LST). Results show that the V-tail configuration greatly affects the aerodynamic characteristics in directional stability as the side force and yaw moment tends to vary linearly with yaw angles up to 25 degrees, compared to conventional tail that has linear characteristics up to only 10 degrees yaw



Edited by:

R. Varatharajoo, F.I. Romli, K.A. Ahmad, D.L. Majid and F. Mustapha




N. A. Musa et al., "Effects of Aircraft Tail Configurations on Sensitivity to Yaw Disturbances", Applied Mechanics and Materials, Vol. 629, pp. 197-201, 2014

Online since:

October 2014




* - Corresponding Author

[1] E. Torenbeek, Synthesis of Subsonic Airplane Design: An introduction to the preliminary design of subsonic general aviation and transport aircraft, with emphasis on design, propulsion and performance. First ed., Delft University Press, Delft , (1996).

DOI: https://doi.org/10.1007/978-94-017-3202-4_9

[2] J. wen, X.Y. Deng, Y.K. Wang, S. Ou, Flow investigation on the directional instability of aircraft with the single vertical tail, Procedia Engineering. 67 (2013) 328-337.

DOI: https://doi.org/10.1016/j.proeng.2013.12.032

[3] F. Nicolosi, P. Della Vecchia and D. Ciliberti, An investigation on vertical tailplane contribution to aircraft sideforce, Aerosp. Sci. Technol. 28 (2013) 401–416.

DOI: https://doi.org/10.1016/j.ast.2012.12.006

[4] W. F. Phillips, A. B. Hansen and W. M. Nelson, Effects of Tail Dihedral on Static Stability, J. Aircraft. 43 (2006) 1829–1837.

DOI: https://doi.org/10.2514/1.20683

[5] P. E. Pursee andJ. P. Campbell, Experimental Verification of a Simplified Vee-Tail Theory and Analysis of Available Data on Complete Models with Vee-Tails. NACA T.N. 823 (1944).

[6] E. C. Polhamus and R. J. Moss, Wind-tunnel Investigation of the Stability and Control Characteristics of a Complete Model Equipped with a Vee Tail. NACA T.N. 1478(1947).

[7] H. Greenberg, Comparison of Vee-Types and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel. NACA T.N. 815 (1941).

[8] G. Q. Zhang,S. C. M. Yu,A. Chienand Y. Xu, Investigation of the Tail Dihedral Effects on the Aerodynamic Characteristics for the Low Speed Aircraft, Adv. in Mech. Engineering. 2013 (2013) 1-12.

[9] M. J. Bamber, and R. O. House. Wind-tunnel Investigation of Effects of Yaw on Lateral-Stability Characteristics I-Four NACA 23012 Wings of Various Plan Forms with and without Dihedral. NACA T.N. 703 (1939).

[10] H. F. Imlay, The estimation of the Rate of Change of Yawing Moment with Sideslip. NACA T.N. 636 (1938).

[11] I. G. Recant, and A. R. Wallace, Wind-Tunnel Investigation of Effect of Yaw on Lateral-Stability Characteristics IV- Symetrically Tapered Wing with a Circular Fuselage having a Wedge-Shaped Rear and a Vertical Tail. NACA Wartime report (1942).

[12] M. J. Abzug, V-tail stalling at combined angles of attack and sideslip, J. of Aircraft. 36(1999)729-731.

[13] R. C. Nelson, Flight Stability and Automatic Control, 2nd. ed., University of Notre Dame: McGraw-Hill International Editions, Boston, (1998).

[14] K. D. Rao, Modelling Nonlinear Features of V-tail Aircraft using MNN, IEEE Aerospace and Electronic System. 31(1995) 841-845.

DOI: https://doi.org/10.1109/7.381934

[15] R. T. Jones, The Influence of Lateral Stability on Disturbed Motions of an Airplane with Special Reference to the Motions Produced by Gusts. NACA T.N. 638 (1938).