DESIGN AND DEVELOPMENT OF A BIFURCATED Y-DUCT INTAKE FOR LIGHT COMBAT AIRCRAFT

摘要

This paper addresses design and development of a high performance wing shielded, short duct air intake for Light Combat Aircraft (LCA). A fixed geometry fuselage mounted intake with a bifurcated Y-duct configuration has been selected. After initially discussing its design features like selected location, boundary layer diverters, throat sizing and duct layout, wind tunnel evaluation towards configuration freeze and establishing engine-intake compatibility are discussed. Some insight into intake flow such as "buzz" and pulse is covered. Full scale intake pressure recovery, from engine ground runs is compared with the estimates and model measurements.