Critical N-Factor behavior in HLFC applications

Abstract

For the development of improved fuselage suction surface concepts for HLFC applications, wind tunnel experiments with multiple suction panels were carried out at DLR by using an aerodynamic flat plate model as a modular test rig, designed for different suction concepts. Studies with multiple porous parts were carried out in 2024 after four previous campaigns. Different panel designs like suction walls, heated surfaces or by traversable hot-wire parts are possible to install. For investigations of fuselage laminarization, staggered suction panels are manufactured, allowing increased transition Reynolds numbers. In the following, results of critical N-factors from linear stability calculations will be compared for multiple suction panels. Various configurations of these panel arrangements were tested with respect to critical N-factor behavior.