Review of the Aerodynamic Acceptance Test and Application to Anti-Icing Fluids Testing in the NRC Propulsion and Icing Wind Tunnel

By: Administration (Nasa), National Aeronaut

In recent years, the FAA has worked with Transport Canada, National Research Council of Canada (NRC) and APS Aviation, Inc. to develop allowance times for aircraft operations in ice-pellet precipitation. These allowance times are critical to ensure safety and efficient operation of commercial and cargo flights. Wind-tunnel testing with uncontaminated anti-icing fluids and fluids contaminated with simulated ice-pellets had been carried out at the NRC Propulsion and Icing Wind Tunnel (PIWT) to better understand the flowoff characteristics and resulting aerodynamic effects. The percent lift loss on the thin, high-performance wing model tested in the PIWT was determined at 8 angle of attack and used as one of the evaluation criteria in determining the allowance times. Because it was unclear as to how performance degradations measured on this model were relevant to an actual airplane configuration, some means of interpreting the wing model lift loss was deemed necessary. In this report, the lift loss was related to the loss in maximum lift of a Boeing 737-200ADV airplane through the Aerodynamic Acceptance Test (AAT) performed for fluids qualification. This report provides a review of the research basis of the AAT in order to understand how this correlation was applied. A loss in maximum lift coefficient of 5.24 percent on the B737-200ADV airplane (which was adopted as the threshold in the AAT) corresponds to a lift loss of 7.3 percent on the PIWT model at 8 degrees angle of attack. There is significant scatter in the data used to develop the correlation related to varying effects of the various antiicing fluids that were tested and other factors. A statistical analysis indicated the upper limit of lift loss on the PIWT model was 9.2 percent. Therefore, for cases resulting in PIWT model lift loss from 7.3 to 9.2 percent, extra scrutiny of the visual observations is required in evaluating fluid performance with contamination. Additional research may result in future changes to this correlation. Broeren, Andy P. and Riley, James T. Glenn Research Center NASA/TM-2012-216014, DOT/FAA/TC-12/32, E-18190, GRC-E-DAA-TN4208 031102.02.02.03.0693.11 WIND TUNNEL TESTS; DEICING; FLUID FLOW; BOEING 737 AIRCRAFT; AERODYNAMIC CHARACTERISTICS; PROPULSION; FLIGHT TESTS; AIRCRAFT ICING; LIFT; PROPYLENE; ETHYLENE; GLYCOLS; PELLETS

• Format: Paperback
• Language: English
• ISBN: B08F6QNSQH
• ISBN13: 9798672729114
• Release Date: January 1
• Publisher: Independently Published
• Length: 40 Pages
• Weight: 0.26 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"