A design method based on tip to tail streamline tracing and osculating inward cone methods is discussed for designing the integrated Osculating Inward Cone Waverider Inlet(OICWI). A practical geometrical constrained experimental model of OICWI is designed based on the validated design method. It has a total contraction ratio of 4.61 and inner contraction ratio is 2.0. Wind-tunnel tests have been conducted for the OICWI model at free stream Mach number(Ma_∞) of 4.0, 3.5 and 3.0 respectively. The experimental results show that the OICWI has high flow capture ratio and compression abilities. It can self-start at Ma_∞= 3.5 and 4.0 and its flow capture ratio is 0.73 at Ma_∞= 4.0, and Angle of Attack(AOA) 0°. The research results show that the OICWI has advantages of inward cone waverider and streamline tracing inlet. Present OICWI is a novel approach for waverider inlet integration studies and it will promote the use of waverider inlet integration configuration in the studies of airbreathing hypersonic vehicles. A design method based on tip to tail streamline tracing and osculating inward cone methods is discussed for designing the integrated Osculating Inward Cone Waverider Inlet (OICWI). A practical geometrical constrained experimental model of OICWI is designed based on the validated design method. It has a The total results show that the OICWI has a high flow rate of 4.61, and the internal contraction ratio is 2.0. Wind-tunnel tests have been conducted for the OICWI model at free stream Mach number (Ma_∞) of 4.0, 3.5 and 3.0 respectively. It can self-start at Ma_∞ = 3.5 and 4.0 and its flow capture ratio is 0.73 at Ma_∞ = 4.0, and Angle of Attack (AOA) 0 °. The research results show that the OICWI has advantages of inward cone waverider and streamline tracing inlet. Present OICWI is a novel approach for waverider inlet integration studies and it will promote the use of waverider inlet integration configuration in the studies of airb reathing hypersonic vehicles.