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The dyed water was placed in 20-gallon tanks, which were connected to six spray nozzles in the IRT. Gelder then taped blotting paper to the airfoil that was to be tested. After the tunnel was operating, a 5- to 10-second spray of water was released into the airstream. The blotter strip was then removed, and a special punch was used to cut out rectangular strips, 0.125 of an inch wide by 1.5 inches long. Each strip was placed in a numbered test tube on a long rack, and distilled water was added. A light beam passing through the mixture would determine the dye concentration in the water.12 The dye impingement research involved a good deal of tedious work for the researchers, and, later, the women who usually did the required hand calculations were brought in to handle the task. Jane Gavlak recalls that Gelder’s strips had to be placed in boiling water to remove the dye. She then had to match the resultant dye against a com- parison chart to determine concentration. Although the work was hard on both eyes and hands, the results were worth the effort. For the first time, the researchers could deter- mine where the droplets were striking and in what concentration. Thus, the principal problem areas that needed icing protection could be identified.13 Although the trajectory studies provided information on the rate that ice would accumulate on an airfoil, NACA researchers still needed reliable data on the shape of the ice formations. Initially, flight tests had been made to measure the aerodynamic penalties caused by various ice shapes. Researchers found that rime icing, primarily associated with low temperatures, had a streamlined shape and did not greatly affect performance. However, heavy glaze icing, associated with high water content and temperatures near freezing, was a different story. Glaze ice formations protruded into the airstream and caused significant aerodynamic penalties.14 The controlled conditions of the IRT allowed researchers to test airfoils of different sizes, thicknesses, and shapes over a wide range of angles of attack and icing conditions. Work done in the early 1950s by von Glahn and Vernon Gray produced drag curves for NACA 63A-009 (6.9-foot chord, 36-inch sweep) and NACA 65-212 (8-foot chord) air- A Golden Age 12 Gelder interview; Gelder, W. H. Smyers, and von Glahn, “Experimental Droplet Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 16 Percent,” NACA TN 3839 (1956). 13 von Glahn, Gelder, and W. H. Smyers, “A Dye-Tracer Technique for Experimentally Obtaining Impingement Characteristics of Arbitrary Bodies and Method for Determining Droplet Size Distribution,” NACA TN 3338 (1955); Leary interview with Jane Gavlak Zager, 27 June 2001. 14 For an excellent summary of the NACA’s icing research during this period, see von Glahn, “The Icing Problem - Current Status of NACA Techniques and Research,” originally presented at the Ottawa AGARD Conference, 10–17 June 1955, and reproduced in “Select Bibliography of NACA-NASA Aircraft Icing Publications,” NASA TM 81651 (1981), pp. 1–10, together with microfiche copies of all important technical papers. 47PDF Image | History of NASA Icing Research Tunnel
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