22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-3.1.1
WIND TUNNEL TESTING OF PERFORMANCE DEGRADATION OF ICE CONTAMINATED AIRFOILS
M.Holl, Z. Pátek, L. Smrcek
(1) VZLÚ, Aeronautical Research and Test Institute, Czech Republic;
(2) Department of Aerospace Engineering, University of Glasgow, Scotland, UK
Keywords: wind-tunnel testing, ice contaminated, airfoil
An experimental investigation was conducted to
study the aerodynamic effect of simulated
supercooled large droplet ice accretion on a
MS(1) 0313 aircraft airfoil by means of wind
tunnel testing. The airfoil was equipped with an
aileron with an axis of movement at 78 % of
airfoil chord. Ice accretion was simulated by a
strip of a quadrantal section with front edge
perpendicular to the surface of the airfoil. Two
strips of different dimensions were examined,
of the height of 1.33 % of chord and 2.25 % of
chord, respectively. Every strip was positioned
at several positions on the upper surface of the
airfoil, and its influence on the basic
aerodynamic characteristics of the airfoil was
evaluated, i. e. the lift, drag, moment and first
of all the hinge moment of the aileron.
The ice accretion strip was positioned
from 5 % to 45 % of chord, the deflections of
aileron were up to 20 degrees down and 30
degrees up and the angle of attack was
changed from 0 up to the angle of maximum
positive and maximum negative lift coefficient.
Wind tunnel tests were performed in the VZLÚ
3 m diameter low - speed wind tunnel at a
Reynolds number of 2.106.
Simulation strips correspond with FAA
recommendation, so data obtained from the
wind tunnel measurements could indicate the
development of aerodynamic characteristics
which can be caused by the phenomenon of ice
accretion under natural conditions, similar
investigation [1]. Standard ice accretion
requirements are described in FAR 25,
Appendix C. It is clear that ice accretion can
lead to large losses in lift, increases in drag and
changes in the pitching moment. Especially
behaviour of the lift and the hinge moment is of
great interest as they are connected closely with
the control of aircraft in complex conditions.
In addition, an experimental investigation
of an ice contaminated airfoil wing glove was
performed in the low speed wind tunnel at the
Department of Aerospace Engineering,
University of Glasgow as part of an ongoing
reseach collaboration between both institutions.
The aim of this programme was to optimise the
wing glove geometry in order to use a UAV
flying laboratory system currently under
development in the Department [8].
view full paper