Mach line cutting of compression surfaces for two-dimensional planar inlets

A forebody design approach based on Mach line cutting of compression surfaces (MLCCS) for 2D planar inlets is presented. The principle behind the methodology is to make use of the supersonic flow characteristics that the disturbances produced by one point propagate within the Mach conoid emanating from this point. A tri-ramp forebody operating at Mach 6 was designed as a demonstration. The results prove that cutting along the Mach line of the compression surface is beneficial to decreasing the drag, whereas the original wedge yields the greatest drag. Also, the cutting affectsK in a detrimental way because their upper surfaces persist to generate negative lifts. Therefore, it is recommended that the upper surface be cut off at least along theMach line of the lower surface.