Abstract: A design method of hybrid airfoil applied in icing wind tunnel test is presented. The method employs the N-S equation to calculate pressure distribution and redesigns the hybrid airfoil derived from a reference airfoil throughout a given angle of attack or α range, with a 15% upper and 25% lower surface of the unchanged shape near leading edge and the shortened chord, aiming at the coincidence of their pressure distributions near the leading edges. A simple influence coefficient and linear interpolation of the control points approach is proposed. The design chord length of hybrid airfoil is shortened by 40% while ensuring the same shape near the leading edge. As the result, the designed hybrid airfoil has the same water droplet impingement characteristics and ice accretion with the reference airfoil. The design theory and results lay the foundation for civil aircraft icing wind tunnel test.