Aerogasdynamics behavior of the escape system separable nose assembly with operating propulsion system

The paper uses computational and experimental data to analyze the behavior of the flow around the separated nose assembly with operating thrusters of the escape system of a manned transportation spacecraft. It demonstrates a significant effect of the jets on aerodynamic characteristics. Distinctive flow regimes have been identified. The feasibility of using the existing software systems for computer simulation of the flow around the separable nose assembly, including the case with operating propulsion system, and for predicting aerodynamic properties in different flight modes. The paper provides data on the comparison of results of computational and experimental studies of aerodynamic properties of the separable nose assembly with inactive propulsion system, which demonstrate the validity of selecting software packages AeroShape-3D and ANsYS CFX for this task. The paper provides profiles of the pressure factor distribution of the surface of the hull and density and flow rate distributions near the nose assembly with both operating and inactive propulsion system in different flow modes. It provides a comparison of jet components of the nose assembly aerodynamic factors obtained through computation with experimental data within the in-flight variation range of Mach numbers from 0,6 to 6,0.