A baseline design for a static-pressure inlet was developed using parametric modeling techniques. Numerical simulations were conducted to investigate the aerodynamic characteristics of the inlet under a freestream Mach number of 0.4. The primary flow structures and flow mechanisms within the inlet were analyzed in detail. Additionally, based on the design concept of a favorable pressure gradient, the key factors affecting the aerodynamic performance of the static-pressure inlet were explored. Results show that the baseline design achieves a total pressure recovery coefficient of σₛ = 0.955 at Mach 0.4. The implementation of the favorable pressure gradient design strategy further improves the aerodynamic performance, increasing the total pressure recovery coefficient to 0.965.