RESUMO

Experimental research results are presented of a self-starting fixed-geometry inlet model intended for supersonic business aircraft propulsion. Two inlet integration schemes with an airframe were considered: (1) an isolated inlet and (2) an inlet in which the generated boundary layer is captured and integrated with a flat plate simulating the nose part of the fuselage. The experiments were conducted in the UV-16 wind tunnel based at the Central Institute of Aviation Motors at M_∞ = 1.8–2.5 and angle of attack α = 0 with and without throttling of the flow in the subsonic diffuser. Various systems of boundary layer control in the inlet were tested: (1) bypassing the boundary layer through windows in the side walls of the inlet with a variable area and (2) bleeding through slots of various configurations in the inlet throat. Based on the experimental data, the inlet throttling performance σ = f(φ), total pressure nonuniformity in the exit cross section of the subsonic diffuser of the inlet, and flow rate of air through the bleeding system are determined. The inlet characteristics with and without the boundary layer simulator are compared.