CRM has extensive experience in computational modeling of core stage, stage separation and booster nozzle flow. Analysis efforts include:

creation of databases determining maximum hinge moments experienced for both the core stage and boosters for the NASA Space Launch System (SLS)
determination of nozzle exhaust for separation events for NASA Ares, Ares 1, and SLS
effects of nozzle flow on lower stage forces and moments during separation
examination of real gas effects for nozzle flow on body integrated forces and moments
analysis of nozzle gimbal effects, including lag between booster and core stage engines
base heating determination
fire-in-the hole separation effects
scarfed nozzle effects

Development of a Maximum Nozzle Hinge Moment Database for SLS

Detailed Analysis of Base Region Flow Physics

Analysis of Boost Deceleration Motors for Ares

Stage Separation Nozzle Exhaust Induced Force and Moment Predictions

Modeling of Nozzle Exhaust Chemically Reacting Flow (Real Gas) Effects

Close-up of injector configuration and diatomic nitrogen iso-surfaces colored with Mach contours

Internal Engine Combustion and Exhaust Modeling

Injector Mach contours, helium mass fraction contours, diatomic nitrogen mass fraction contours