In this study, the application of direct current arc plasma discharge is discussed through computational analysis on the flow around a bump-up shape over a surface of a typical hypersonic vehicle under 20-km altitude and Mach-5 flight condition. Numerical simulation based on our simple plasma model suggested that the front pressure over a bump-up slope could be decreased by the use of plasma actuation method proposed in this study. The plasma source generated at 7 cm ahead of the bump successfully reduced the drag coefficient for more than 56%, changing the surface flow to go smoothly along the surface of the bump shape.