Numerical and Experimental Studies on Characteristics Under Angle of Attack for Forebody-Inlet

In order to study the characteristics of external and internal flow field for forebody-inlet,the united model was simulated. The numerical method has been proved by the comparison between numerical results and the test data. The forebody influence on inlet entrance and internal flow was analyzed at different angles of attack. Furthermore,the angle of attack influence on total pressure recovery coefficient and distortion index was researched. The results show that ventral mounted layout can reduce the angle of attack and Mach number at inlet entrance for high angle of attack,which can improve flight limit. The total pressure recovery coefficient can achieve 0.94 in a broad range of angle of attack under supersonic flow. When angle of attack range is between 9 ° and 18 °,the inlet has a low-level total pressure distortion. However,the total pressure distortion is sensitive to the change of angle of attack when the angle is out of range described above.