This thesis compares the influence of the angles of attack (α) and yaw (β) on the inlet performance with the underfuselage inlet and the fuselage side inlets by means of low and high speed wind tunnel tests.The results show that in supersonic flow the aerodynamic performance of the underfuselage inlet becomes better when the angle of attack changes from 0 to 5°

but that of the fuselage side inlets remains almost unchanging.In subsonic flow when the angle of attack changes from 6° to 12° (high subsonic) or 30° (low speed)

the performance of the fuselage side inlets becomes worse obviously

but that of the underfuselage inlet almost does not change with the angle of attack and can be kept the same as α=0°.In high and low speed free stream flow

the performance of two kinds of inlets almost does not change with β.