This paper presents the results of numerical and experimental study of subsonic intake, integrated with curvilinear fuselage fore body under subsonic flowing. Numerical research of air intake flow and performance were obtained at different throttle modes and turbulence models at flight altitude H = 0 ÷ 0.5 km and Mach number M = 0.4. An experimental research was performed in wind tunnel of Central Institute of Aviation Motors at M = 0.4, an attack angle = 0 and Reynolds number Re = 1.8 × 10 6. The losses of total pressure at the different throttle modes, distribution of the static pressure along the intake and fuselage length were determined. Satisfactory agreement between calculated and experimental data was obtained. A flow control air intake methods are proposed.