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Using a droplet size of 160 microns, Ide, who was responsible for calibrating the tunnel’s icing cloud for droplet size, liquid water content, and cloud uniformity, ran a special series of calibration tests. Although he did not have time to calibrate the 160- micron-diameter cloud at various liquid water contents for given airspeeds, he was satisfied that the tunnel simulation would produce accurate results.7 The first series of experiments employed a Twin Otter wing section. Researchers subjected the aluminum airfoil with a constant chord of 77.25 inches to an array of large droplet icing conditions, including variations in temperature, airspeed, droplet size, angle of attack, pneumatic boot cycle interval, and flap settings. They found that an ice ridge formed aft of the de-icer boot on every experimental icing run. The ridge was sensitive to changes in temperature, reaching a maximum size at 28°F for 125 miles per hour and 30°F for 195 miles per hour. Variations in boot cycling time did not have a significant effect on the residual ice accretion. A second series of IRT tests were performed on a NACA 23012 wing section. This tapered airfoil was mounted vertically in the test section and had a chord length which varied from 73.8 inches at the floor to 65.2 inches at the ceiling. Technicians outfitted the leading edge of the model with a full-span pneumatic de-icer boot that extended to 6 percent of the chord on the suction surface and to 11 percent on the pressure surface of the airfoil. Researchers Addy and Miller selected the following “anchor points” for the tests: 32°F, 160 microns, 0.82 grams per cubic meter LWC, 195 miles per hour, 0° angle of attack, 3 minutes boot cycle, and 18 minutes spraying time. They then investigated the effects of each one of the anchor points while holding the other points steady. For example, what would be the effect on the airfoil of lowering the temperature to 28°F while all other conditions remained unchanged for the anchor points? As in the previous Twin Otter study, researchers discovered that temperature had the most significant impact on ice accretion. While holding the other parameters constant at their anchor points, the researchers ran tests at temperature ranges of 5°F to 37°F. At 37°F, all impinging water ran back to the trailing edge and was blown off the airfoil. Ice began to form at 34°F, with a distinct ridge just aft of the active portion of the boots on both suction and pressure surfaces. At temperatures below 30°F, the ridge appeared to harden and become more resistant to shedding. The largest ice ridge—over 1 inch in height—occurred in temperature ranges of 24°F through 28°F. Tests on the Twin Otter and NACA 23012 airfoils, the researchers concluded, yielded “valuable information, as well as a substantial database on large droplet ice accre- New Challenges 7 Harold E. Addy, Jr., Dean R. Miller, and Robert F. Ide, “A Study of Large Droplet Ice Accretion in the NASA Lewis IRT at Near Freezing Conditions; Part 2,” NASA TM 107424 (1996). 137PDF Image | History of NASA Icing Research Tunnel
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