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The Rolling Moments due to Sideslip on High Tailplanes at Subsonic and Transonic Speeds

Published online by Cambridge University Press:  04 July 2016

D. G. Mabey
D. G. Mabey*
Affiliation:
Royal Aircraft Establishment, Bedford
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Extract

Some measurements in the R.A.E. Bedford 3 ft. wind tunnel on a typical high tailplane illustrate a Mach number effect on the tailplane rolling moments due to sideslip which has been apparently overlooked previously. Fig. 1(a) shows that the increase in tailplane rolling moment due to sideslip is much larger than the increase in the fin lift curve slope a1F, Fig. 1(b). This extra increase in rolling moment is associated with the increase in the tailplane lift curve slope a1T, Fig. 1(c). In fact the rolling moment on this high tailplane varies roughly as the product of the fin and tailplane lifts, as Fig. 1(d) shows. A qualitative explanation follows.

Consider the idealised high tailplane shown in Fig. 2. At zero geometric incidence and positive sideslip the fin lift will induce positive and negative incidence distributions on the starboard and port sides of the tailplane.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 64 , Issue 591 , March 1960 , pp. 161 - 163
Copyright
Copyright © Royal Aeronautical Society 1960

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References

1.Stanbrook, A. S. (1954). The Lift Curve Slope at Subsonic and Supersonic Speeds. Aircraft Engineering, Vol. 26, p. 244, August 1954.CrossRefGoogle Scholar
2.Queijo, M. J. and Riley, D. R. (1954). Calculated Sub sonic Span Loads and Resulting Stability Derivatives of Unswept and 45° Swept Surfaces in Sideslip and Steady Roll. N.A.CA. T.N. 3245, October 1954.Google Scholar
3.Weber, J. and Hawk, A.C. (1954). Theoretical Load Distributions on Fin-Body-Tailplane Arrangements in a Side Wind. R. & M. 2992, ARC 17413, August 1954.Google Scholar
4.McGowan, W. A. (1959). An Analysis of Incremental Horizontal-Tail Loads Measured on a Swept-Wing Bomber Airplane in Sideslip Maneuvers. N.A.S.A. T.N. D-100, October 1959.Google Scholar