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Spin induced aerodynamic flow conditions on full-scale aeroplane wing and horizontal tail surfaces

Published online by Cambridge University Press:  27 January 2016

R. I. Hoff  and
G. B. Gratton
R. I. Hoff*
Affiliation:
Brunel Flight Safety Laboratory, School of Engineering and Design, Brunel University, Uxbridge, Middlesex, UK
G. B. Gratton*
Affiliation:
Brunel Flight Safety Laboratory, School of Engineering and Design, Brunel University, Uxbridge, Middlesex, UK
*
[email protected]
[email protected]
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Abstract

The aerodynamic flow conditions on wings and tail surfaces due to the rotational motion of a spinning aeroplane have been investigated in a full-scale spin flight research programme at the Brunel Flight Safety Laboratory. The wing upper surface vortex has been visualised using smoke and tufts on the wing of a Slingsby Firefly. The flow structures on top of both wings, and on top of the horizontal tail surfaces, have also been studied on a Saab Safir. The development of these rotational flow effects has been related to the spin motion and the effect on the spin dynamics has been studied and discussed. Evidence suggests that the turbulent wake from the wing upper surface vortex impinges the tail of the aircraft during the spin entry. It is hypothesised that the turbulent flow structure on the outside upper wing surface is due to additional accelerations induced by the rotational motion of the aeroplane. Furthermore, the lightening in stick force during spin entry and the apparent increase in push force required for spin recovery corresponds to the observed change in flow condition on the horizontal tail. The difference in pressure on the upper and lower horizontal tail surfaces have been measured using differential pressure sensors, and the result corresponds both with the observed flow conditions and earlier research results from NASA.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1198 , December 2013 , pp. 1207 - 1231
Copyright
Copyright © Royal Aeronautical Society 2013 

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