新型飞行器表面存在微烧蚀现象，会导致壁面局部热流增大。采用粗糙高度小于600 μm的波纹型粗糙来模拟微烧蚀表面。通过直接求解Navier-Stokes方程，计算了均布波纹粗糙的壁面峰值热流的变化规律。结果发现，粗糙度引起的峰值热流与流向位置的0.5次方成反比；壁面峰值热流与粗糙高度成正比，并随宽度增大而减小，受高度的影响大于宽度。同时，马赫数和壁温对壁面峰值热流影响结果表明，相对峰值热流增量与马赫数成反比、与壁温成反比。在此基础上，基于光滑平板热流理论解，给出了粗糙壁峰值热流预测公式。详细的工况验证表明，该公式在马赫数4~10和壁温300~800 K范围内能够准确预测粗糙壁面峰值热流，误差不超过8%。对于其他壁面形式，如椭圆型和分散正弦型，该公式也具有一定的适用性。

Micro ablation on the surface of new-type vehicles will lead to increased local heat flux on the wall surface. This study uses corrugated roughness with roughness height smaller than 600 μm to simulate micro ablative surfaces， and calculates the variation law of the peak heat flux on the wall surface with uniform corrugated roughness by directly solving the Navier-Stokes equation. It is found that the surface peak heat flux caused by roughness is inversely proportional to the 0.5 times of the flow position， the surface peak heat flux is proportional to the roughness height and decreases with increasing width， and is more influenced by the height than the width. Meanwhile， the influence results of the Mach number and wall temperature on the surface peak heat flux at the wall show that the relative surface peak heat flux increment is inversely proportional to both the Mach number and wall temperature. Further， based on the smooth flat plate heat flux theory solution， we provide the surface peak heat flux prediction formula. Detailed verification of the working conditions reveals that the formula can accurately predict the surface peak heat flux in the range of Mach number 4-10 and wall temperature 300-800 K with an error of no more than 8%. For other wall forms， such as elliptical and dispersive sine types， the formula can also produce an accurate prediction.