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

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Periodical:

Edited by:

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

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197-201

Citation:

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

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