Abstract
Nomenclature Major modifications are planned in the 6 ft by 9 ft (1.8 m by 2.7 m) Icing Research Tunnel (IRT) at the NASA Lewis Research Center, including replacement of its heat exchanger and associated ducts and turning vanes, and the addition of fan outlet guide vanes (OGVs). A one-tenth scale model of the IRT (designated the SMIRT) with and without these modifications was constructed and tested. to increase confidence in obtaining expected improvements in flow quality around the tunnel loop. This paper describes the SMIRT as an aerodynamic test facility, and its qualification as a scaled representation of the flow patterns in the IRT. Test data defining flow profiles across a representative cross-section downstream of the fan are presented for both the IRT in its current (baseline) configuration and for the SMIRT in both baseline and modified configurations, with and without simulated OGVs. Flow distribution in the SMIRT is shown to be an accurate representation of that in the IRT. In addition, the simulated OGVs greatly improved the uniformity of flow downstream of the SMIRT fan, leading to the projection that the installation of fan OGVs in the IRT may reduce current flow distortions immediately downstream by two thirds. Future papers are planned to present flow quality test data at other sections of the SMIRT with and without simulated OGVs. COV Coefficient of Variation D Diameter of Fan H Height of Duct IRT Icing Research Tunnel (6 x 9') L Length of Baffles Around SMIRT Fan Motor Nacelle OGV Outlet Guide Vane r Radial Coordinate (Figure 8(a)) SMIRT Scale Model Icing Research Tunnel Uavg Average Axial Velocity within a 5-deg (0.09 radians) sector Umean Mean Axial Velocity in Cross Section Ustd Standard Deviation of Axial Velocity Measurements in Cross Section W Width of Duct y Horizontal Distance from Inner Wall Y y/W z Vertical Distance from Floor Z z/H Azimuthal Coordinate (Figure 8(a)) $avg Average of Azimuths within a 5-deg (0.09 radians) sector
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