Flow quality studies of the NASA Lewis Research Center Icing Research Tunnel

Abstract

A series of studies have been conducted to determine the flow quality in the NASA Lewis Icing Research Tunnel. The primary purpose of these studies was to document airflow characteristics, including flow angularity, in the test section and tunnel loop. A vertically mounted rake was used to survey total and static pressure and two components of flow angle at three axial stations within the test section (test section inlet, test plane, and test section exit; 15 survey stations total). This infonnation will be used to develop methods of improving the aerodynamic and icing characteristics within the test section. The data from surveys made in the tunnel loop were used to determine areas where overall tunnel flow quality and efficiency can be improved. A separate report documents similar flow quality surveys conducted in the diffuser section of the Icing Research Tunnel. 1

Modeling In-Flight Ice Accretion Under Uncertain Conditions

“…Table 2 reports the experiment nominal conditions together with the uncertainty maximum and minimum bounds. Uncertainty bounds are established according to the IRT calibration report [52]. The goal is to propagate the uncertainty affecting the parameters of the experiment namely, the angle of attack AoA, the mach number 𝑀, the free stream pressure and temperature 𝑃 ∞ and 𝑇 ∞ and the MVD, to the numerical predictions of the collection efficiency over the airfoil surface.…”

Flow Quality Surveys in the Settling Chamber of the NASA Glenn Icing Research Tunnel (2011 Tests)

“…In order to improve the quality of data, testing was done near the IRT's maximum velocity capability. Previous tests have shown that the loop flow quality does not vary much with test section velocity [7], and so only one velocity was used for this test. This velocity was also chosen because it was used for the tests in 2000.…”

Flow Angularity Investigations in an Automotive Slotted Wall Wind Tunnel

“…However, investigations of the causes of flow angularity in the test section are less common. Arrington et al [16] performed measurements of flow angularity in the test section of a subsonic icing tunnel, as well as measurements at a number of stations throughout the wind tunnel circuit. Their investigations showed that the cooler mounted between corners three and four induced some angularity, but that its influence could not be seen in the settling chamber.…”