Shock Angle Characteristics and Test Analysis of Hypersonic Wide-Speed-Range Cruise Aircraft

Hypersonic aircraft represent a cutting-edge technology in aerospace engineering, where the shock angle serves as a critical aerodynamic parameter. However, existing studies remain limited by significant prediction errors for the shock angle. This study employs a combination of numerical simulation and wind tunnel test techniques to analyze the shock angle characteristics of hypersonic wide-speed-range cruise aircraft. Consequently, a numerical simulation analysis model for the shock angle of such aircraft was established. Shock angle measurement tests were conducted at various Mach numbers in a pulsed combined high-enthalpy wind tunnel. Comparing the simulation results to the wind tunnel results revealed a numerical error of 4.08%, validating the accuracy of the numerical model. Shock angles at Mach numbers 6, 7, 8, 9, 10, 12, 15 and 20 were analyzed in the numerical simulations, and a nonlinear fitting method was used to determine the functional relationship between the shock angle and Mach number. The results indicate that as the Mach number increases, the shock angle progressively decreases, and its attenuation rate diminishes. The shock angle exhibits an exponentially decreasing relationship with the Mach number, approaching 10.708° as the Mach number approaches infinity. This study provides methodological support and data references for predicting shock wave characteristics and designing aerodynamic hypersonic aircraft.