Numerical Investigation and Surrogate Modeling of Aerodynamic Jet Interaction for Continuous Type Side-Jet Controlled Rocket

Abstract

The supersonic jet interaction generated by a continuous type side-jet thruster of the missile was considered. Firstly, the jet interaction flow field was investigated using numerical simulations. The simulation was made use of the three-dimensional unstructured-based computational fluid dynamics (CFD) solver. The numerical simulation method was validated through comparison with wind tunnel test results. Flow fields investigation and jet interaction effects for various flow conditions, jet magnitude, and jet direction conditions were performed. Secondly, the jet interaction aerodynamic database based on CFD data was developed and assessed. The generation of the jet interaction aerodynamic database for the continuous type side-jet requires a large amount of simulation data owing to the complex nature of jet interaction. To reduce the required number of simulations, seven jet operating conditions were selected using geometrical symmetry at first

then, three-dimensional numerical simulations were conducted to build the jet interaction aerodynamic database in the reduced design space. Two modeling approaches were used in developing the jet interaction aerodynamic database. One is CFD-based modeling with a full factorial sampling, and the other is surrogate modeling, based on the Latin hypercube sampling and Kriging method, for the interim database. The resulting two aerodynamic databases were assessed through comparison with flight test results. Based on the comparison, both models showed a suitable representation of the aerodynamic coefficients within 10\% error during the jet operation period. This assessment confirms that the jet interaction aerodynamic database for missiles with continuous type side-jet thruster can be constructed using the CFD-based modeling approach. The surrogate model was found to perform well compared with the CFD-based model within an acceptable error level.