Numerical Simulations of Two-Dimensional Hypersonic Inlet At Finite Flight Angles

Considering the angle of attack of the missile using solid rocket ramjet changes in large range, this paper adopts the method of numerical simulation, study how the angle of attack influences the inlet flow field characteristics and performance parameters, and analyzes the mechanism of its formation based on the basic theory of aerodynamic, providing the necessary reference for the inlet design and performance estimation. At both positive and negative angles of attack, the total pressure recovery at the outlet decreases. With the increase of the angle of attack, the outlet pressure increases, while the outlet Mach number decreases, and the captured mass flow rate increases. When the angle of attack increases to a certain extent, the captured flow rate in the throat will be choked, and the inlet works in unstarting mode.