An experimental investigation has been carried out.The influences of attack angle (α=0°～45°) and yaw angle (β=-15°～+15°) on caret inlet gas-dynamic performance were investigated experimentally.The variation of the inlet performance parameters with the attack angles

as well as total pressure contour plots of inlet/exit at typical states

have been presented

and the relationship between flow characteristics of the inlet and its exit total pressure contour plots has also been analyzed.It is shown that

in the condition of low speed incoming flow (Ma≈0 1)

the inlet total pressure recovery coefficient decreases slowly with the increase of attack angle (α=0°～45°)

and the total pressure distortion is nearly unchanging.As a result

caret inlet is favorable to maneuver flight at large attack angle.With zero attack angle and at same exit Mach number

the yaw angle has a great influence on position of inlet/exit higher and lower total pressure domains

i.e.the whole exit flow field rotates clock-wise as the yaw angle increases (β=-15°～+15°).However

the influence of the yaw angle becomes weaker with the increase of attack angle.