Abstract: In order to realize the rapid evaluation and optimization for general configurations of civil aircraft, a prediction model based on physical mechanism of aircraft noise was established for the leading edge slat and the trailing edge flap of the civil aircraft high lift device, and the corresponding noise prediction system named UNICRAFT was developed. In order to evaluate the calculation accuracy and efficiency of the tool UNICRAFT, this article focused on two general configurations. One was the wing hanging layout configuration, including the leading edge slat and Fowler flap. Another was the tail hanging layout configuration, which includes the leading edge slat and the receding flap with fixed sub-flap. The noise levels of both configurations have been calculated and verified. Finally, the effectiveness of the prediction tools for aircraft-level noise was verified by the comparison with the results of acoustic wind tunnel tests and prediction.