Wind Tunnel Testing of Ice Roughness Effect on UTM Half Model
Keywords:
Ice roughness, swept wing, UTM half model, aerodynamic performanceAbstract
Ice accretion effect on the aircraft is a great threat to flight safety. The impact on flight performance is detrimental that it could lead to catastrophic event. This research was carried out to investigate the effect of ice roughness on a three-dimensional (3D) swept wing of the Universiti Teknologi Malaysia (UTM) half model (aircraft) by using a wind tunnel facility. The ice roughness model with different heights was replicated on the leading-edge of the half model swept wing. The test was conducted at the UTM Aerolab Low Speed Tunnel considering low Reynolds number. The UTM half model was configured at three different flap angles to simulate the flight phase of take-off, cruise and landing. The results from the semi-span component balance were analysed and compared with the clean model as baseline. The aerodynamic performance penalty was observed to be substantial. The performance loss was more severed with higher ice roughness height and the finding is in agreement with the published literature for wind tunnel testing of a 3D swept wing.References
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