An Adverse Environment Rotor Test Stand (AERTS) has been designed, and constructed. The facility is able to reproduce natural icing conditions on a hovering rotor. The motor/hub configuration is designed to spin instrumented rotors of up to 9 ft. diameter and has the capability of providing tip speeds of up to 470 ft/sec. A Liquid Water Content (LWC) calculation methodology was developed and sensitivity studies to determine experimental LWC are presented in this paper. Correlation between experimental ice accretion shapes obtained in the AERTS facility and experimental results obtained by the NASA Icing Research Tunnel and the Air Force Arnold Engineering Development Center are presented. These experimental correlations are conducted to demonstrate the capability of producing an accurate realistic icing cloud of the new facility. All tests reported in this paper have been conducted on 1 in. diameter circular cross section rotors. The majority of the experimental ice shapes compared agree with results presented in literature with thickness errors as low as 2% and impingement limits discrepancies no greater than 15%.
|Original language||English (US)|
|Number of pages||15|
|Journal||Annual Forum Proceedings - AHS International|
|State||Published - Dec 1 2010|
|Event||66th Forum of the American Helicopter Society: "Rising to New Heights in Vertical Lift Technology", AHS Forum 66 - Phoenix, AZ, United States|
Duration: May 11 2010 → May 13 2010
All Science Journal Classification (ASJC) codes