Hybrid wing design to match full-scale wing ice accretion

Sudhindra Uppuluri, Michael S. Selig

Research output: Contribution to conferencePaperpeer-review

Abstract

A hybrid wing design methodology has been formulated to provide guidance in designing hybrid wings that simulate the droplet impingement and ice accretion of full-scale wings. The hybrid wing in this context has a smaller chord than the full-scale wing and hence can be easily tested in the existing icing tunnels which are too small to perform ice accretion testing of full-scale commercial aircraft wings. This paper presents a systematic study to design hybrid wings based on the hybrid airfoil design methodology that has been previously developed and validated by Saeed et al. The new wing design methodology involves understanding the effect of various factors causing three dimensionality in the flow such as induced effect and spanwise flow on ice accretion. Three wing configurations with increasing three-dimensionality in the flow were analyzed at various angles of attack. The ice accretions on the full-scale and hybrid wings were compared, and the hybrid wing was modified, if necessary, using aerodynamic twist or flap to match the leading edge flowfield and hence ice accretion of the full-scale wing.

Original languageEnglish (US)
DOIs
StatePublished - 2002
Event40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
Duration: Jan 14 2002Jan 17 2002

Other

Other40th AIAA Aerospace Sciences Meeting and Exhibit 2002
CountryUnited States
CityReno, NV
Period1/14/021/17/02

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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