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A Correlation for the Effect of Control Deflection upon Pitching Moment

Published online by Cambridge University Press:  04 July 2016

J. C. Gibbings
J. C. Gibbings*
Affiliation:
Fluid Mechanics Division, Department of Mechanical Engineering, University of Liverpool
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Extract

The rate of change of the pitching moment coefficient upon an aerofoil with respect to the deflection of a flap control—a quantity denoted by m2—is of interest in its effect upon the torsional twisting of an aerofoil and hence upon the wing reversal phenomenon. The value of m2 is very susceptible both to small aerofoil profile modifications and to boundary layer conditions. As a result this quantity is not very amenable to attempts to correlate experimental values and this is particularly so for the small values of the control chord that are typical of control tabs.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 69 , Issue 659 , November 1965 , pp. 793 - 794
Copyright
Copyright © Royal Aeronautical Society 1965

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References

1.Garner, H. C. Charts for Low-Speed Characteristics of Two-Dimensional Trailing-edge Flaps. ARC R & M 3174, 1960.Google Scholar
2.Glauert, . Theoretical Relationships for Aerofoils with Flaps. R & M 1095.Google Scholar
3. The Royal Aeronautical Society. Aerodynamic Data Sheets. Controls 08.01.01.Google Scholar
4.Ames, M. B. JR. and Sears, R. I. Pressure Distribution In vestigation of a NACA 0009 Airfoil with a 30% Chord Plain Flap and Three Tabs. NACA Tech Note 759.Google Scholar
5.Street, W. G. and Ames, SR., M. B. Pressure Distribution Investigation of a NACA 0009 Airfoil with a 50% Chord Plain Flap and Three Tabs. NACA Tech Note 734.Google Scholar
6.Beavan, J. A., Hyde, G. A. M. and Fowler, R. G. Pressure and Wake Measurements up to Mach Number 085 on an EC 1250 Section with 25% Control. ARC R & M 2065.Google Scholar
7.Hilton, W. F. and Knowler, A. E. Lift and Pitching Moment Measurements on an EC 1240 Tailplane Elevator at High Speeds with Elevator Gap Sealed. ARC R & M 2227.Google Scholar
8.Wenzinger, C. J. and Delana, J. B. Pressure Distribution over an NACA 23012 Airfoil with a Slotted and a Plain Flap. NACA Rep 633.Google Scholar
9.Hughes, G. F. Measurements of Twisting Moment Due to Aileron Deflection on a Model Mustang Wing at High Speeds. RAE Tech Note Aero 1805.Google Scholar