Three-Dimensional Computational Analysis of Complex Launch Vehicle Configurations

Computational fluid dynamic analysis is performed on the Conestoga 1620 vehicle configuration at Mach 0.8 and 1.49 points along its ascent trajectory. Because the vehicle geometry is complex, flow solutions were obtained using a technique where overlapping volume grids are generated over each individual component. Calculations were performed to evaluate the pressure loading on the structural components, compute aerodynamic drag, and determine the effect the pressure distribution would have, if any, on booster separation. Pressure loading on the wire tunnels was found to exceed original design limits, and the wire tunnels were strengthened as a result of this study. There was no evidence of flow impingement on the motor nozzles. Pressure forces on the strap-on boosters do not appear as though they will hinder booster separation.