The Icing Research Tunnel is used extensively to test many classes of aircraft under atmospheric icing conditions. Because of the need to test models at higher Reynolds numbers, a new fan rotor was designed to increase test section wind speed. A preliminary study was made of the present fan rotor to suggest possible methods to increase tunnel wind speed. The results of that study are presented.
Calculated Performance of the NASA Lewis Icing Research Tunnel
1991
23 pages
Report
No indication
English
Laboratory & Test Facility Design & Operation , Test Facilities & Equipment , Aircraft hazards , Computer programs , High reynolds number , Ice formation , Rotor aerodynamics , Rotors , Turbofans , Computerized simulation , Man-computer interface , Reynolds number , Test chambers , Wind tunnels , Wind velocity
The New Icing Cloud Simulation System at NASA Lewis' Icing Research Tunnel
British Library Conference Proceedings | 1998
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