Advanced computational models which solve the full (FNS) and parabolized (PNS) Navier-Stokes equations for the analysis of missile aerodynamic problems with exhaust plume interactions are described. The models utilize conservative implicit algorithms and include finite-rate chemistry, two-equation turbulence models, and preliminary multi-phase flow capabilities. In the tactical missile arena, a 3D Navier-Stokes code, PARCH, was developed to analyze missile/plume interactions with both conventional nozzle exhausts, as well as with bifurcated/scarfed nozzle exhausts. The PNS work has focused on supersonic/hypersonic applications utilizing time-iterative upwind numerics for enhanced robustness and accuracy, and has included the analysis of aerodynamic, plume, and propulsive problems for missiles as well as for reentry and aerospace vehicles.
Computational Models with Advanced Thermochemistry for the Analysis of Missile/Plume Flowfield Interactions
1990
30 pages
Report
No indication
English
Missile Trajectories & Reentry Dynamics , Aerodynamics , Flow distribution , Missiles , Navier-Stokes equation , Plumes , Turbulence models , Mathematical models , Thermochemistry , Aerospace vehicles , Algorithms , Exhaust gases , Hypersonics , Multiphase flow , Reentry vehicles , Robustness (Mathematics) , Supersonics
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