TRANAIR, a non-linear full potential solver with a coupled boundary layer code was used as the main tool in the design and optimization process of the three-dimensional glove shape. Therefore, once an initial glove geometry is created from the airfoil, the three dimensional wing glove has to be optimized to ensure that the desired extent of laminar flow is maintained over the entire glove. The airfoil design process does not consider the three dimensional flow effects such as cross flow due wing sweep as well as engine and body interference. The process of designing a laminar flow wing glove starts with creating a two-dimensional optimized airfoil and then lofting it into a three-dimensional wing glove section. (paper)Ĭomputational Optimization of a Natural Laminar Flow Experimental Wing GloveĬomputational optimization of a natural laminar flow experimental wing glove that is mounted on a business jet is presented and discussed. The results indicate that the sensitivity of the flow to the disturbances, which can translate into manufacturing tolerances, was similar to that of subsonic natural laminar flow wings. Despite the unwanted crossflow, the airfoil performed well. A series of oblique shocks, of yet unknown origin, appeared on the surface, which generated sufficient crossflow to affect transition. Both discrete (trip dots) and 2D disturbances (forward-facing steps) were tested. The objectives of the tests were to determine the extent of laminar flow at high Reynolds numbers and to determine the sensitivity of the flow to disturbances. The tests were flown up to Mach 2.0 and chord Reynolds numbers in excess of 30 million. An aircraft-mounted infrared camera system was used to determine boundary layer transition and the extent of laminar flow. The test article surface was coated with an insulating material to avoid significant heat transfer to and from the test article structure to maintain a quasi-adiabatic wall. The test article was designed with a leading edge sweep of effectively 0° to minimize boundary layer crossflow. The test surface was an 80 inch (203 cm) chord and 40 inch (102 cm) span article mounted on the centerline store location of an F-15B airplane. International Nuclear Information System (INIS)įrederick, M A Banks, D W Garzon, G A Matisheck, J RĪ flight test campaign of a supersonic natural laminar flow airfoil has been recently completed. Flight tests of a supersonic natural laminar flow airfoil
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