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A Two-Dimensional Aerofoil with a Control Surface Oscillating at Low Frequency in High Subsonic Flow

Published online by Cambridge University Press:  07 June 2016

D Nixon
D Nixon*
Affiliation:
Queen Mary College, University of London
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Summary

The aerodynamic derivatives for a two-dimensional aerofoil with an oscillating control surface in a high subcritical flow are calculated using the method of Nixon. The aerofoil is assumed to be symmetric and at zero incidence with a zero mean control surface deflection angle. With the exception of the control surface stiffness derivative the magnitudes of the aerodynamic derivatives are greater than the corresponding linear values by between 15–35 per cent; the greatest difference occurs for low values of the frequency parameter. The magnitude of the control surface stiffness derivative is less than the corresponding linear value by the order 10–15 per cent.

Type
Research Article
Information
Aeronautical Quarterly , Volume 25 , Issue 3 , August 1974 , pp. 186 - 198
Copyright
Copyright © Royal Aeronautical Society. 1974

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References

1 Dietze, F, Die Luftkrafte des harmonisch schwingenden Flugels in kompressiblen Medium bei Unterschallgeschwindigkeit. DVL Forschungsbericht 1733, 1943.Google Scholar
2 Nixon, D, A two-dimensional aerofoil oscillating at low frequency in high subsonic flow. ARC Current Paper 1285, 1974.Google Scholar
3 Nixon, D, Hancock, G J, High subsonic flow past a steady two-dimensional aerofoil. ARC Current Paper 1280, 1974.Google Scholar
4 Nixon, D, The high subsonic flow around a two-dimensional aerofoil with a trailing-edge control surface. Aeronautical Quarterly, Vol XXIV, p 273, November 1973.Google Scholar