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Abstract Certain aircraft configurations use embedded gas turbine engines that require offset inlets to direct oncoming air to the engine face. Y-duct inlets are commonly used, especially in military aviation, due to their versatility and aerodynamic performance. Work completed at the Royal Military College of Canada has investigated the performance of two Y-duct designs to study the effect of certain geometric parameters on duct performance. A baseline duct was created and its performance was evaluated at an entrance Mach number of Ma = 0.63. The baseline duct was originally designed for Ma = 0.80 entrance flow; however, the flow choked in the Y-duct at Ma = 0.63. A modified Y-duct was then created by reducing offset and bends in the baseline geometry to overcome the problem. Static and total pressure recovery were evaluated at Ma = 0.8 to determine the presence of secondary flows in the modified duct. This work aims to develop the understanding of relationships between geometric parameters and performance of Y-duct inlets.
Gilbart et al. (Mon,) studied this question.