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Impinging jet is widely implemented at the leading edge of aircraft wings for anti-/de-icing purposes. To further improve the anti-icing performance, this paper utilized numerical simulation to explore the impingement heat transfer characteristics of different fin arrays on flat plate and concave surface sequentially. The fin array in the flat-plate model consisted of 8, 12 straight fins or 12 curved fins. The concave surface model consisted of 8 short or long fins. The results show that the addition of fin arrays on the flat plate and airfoil surface can significantly improve the jet impact heat transfer performance at different Reynolds numbers. Compared with non-fins, the comprehensive heat transfer effect on the airfoil surface is increased by 4%—10%, especially for the stagnation region. Further flow field analysis reveals that adding fin array not only increases the area of heat transfer, but also strengthens the turbulent kinetic energy of impingement jet flow, leading to an enhancement of heat transfer performance.

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• A "stream-wise plasma heat knife" configuration was proposed based on nSDBD for better anti-icing performance. • Wind tunnel experiments were conducted to study quantitatively the performance of the "stream-wise plasma heat knife". Spatial-temporal distribution and the dynamic process of icing on a NACA0012 airfoil were obtained. • An analysis of the balance between discharge energy and anti-icing energy was introduced. • A good agreement between analytical results and existing experiments was achieved, providing a good prediction of the anti-icing performance for nSDBD based plasma anti-icing devices. Ice accretion is one of the potential dangers of the aircraft. Surface dielectric barrier discharge (SDBD) based plasma anti-icing is one of the novel methods that has the advantage of energy efficient, fast response and geometrical simplicity. A "stream-wise plasma heat knife" configuration was proposed based on nanosecond pulsed SDBD for better anti-icing performance. A set of wind tunnel experiments were conducted to study the performance of the "stream-wise plasma heat knife" quantitatively. Spatial-temporal distribution and the dynamic process of icing on a NACA0012 airfoil model were obtained. An analysis of the balance between discharge energy and anti-icing energy was introduced, an energy efficiency η total ≈ 15.6–21.6% was found to be appropriate as the ratio between heating energy and total deposited energy during discharge. A good agreement between analytical results and existing experiments was achieved, providing a good prediction of the anti-icing performance for nSDBD based plasma anti-icing devices. [ABSTRACT FROM AUTHOR]