Computational Challenges in Simulating Powered Flight of the Orion Launch Abort Vehicle (Invited)

Some of the simulation work performed by the computational aerosciences project under the NASA Constellation program is presented. The challenges of simulating the powered ight of the Orion launch abort vehicle for the purposes of building an aerodynamics database are discussed. During an abort this vehicle res both a four-nozzle abort motor together with an eight-nozzle attitude control motor. The interactions of the jet plumes provide a signicant challenge to the computational tools. A few of the computed results using overset grids and the Overow solver are presented. Some very complex behavior in the jet plumes was observed, including asymmetric yaw-inducing plume interactions. The problem of jet-plume simulation was studied using a simpler jet-in-crossow problem. A number of these simulations also produce asymmetric results for a completely symmetric problem. The results from the use of dierent turbulence models, dierent grid resolution, and various dierencing schemes are presented for the jet-in-crossow problem. All steadystate cases are shown to be asymmetric, while time-averaged solutions from time-accurate simulations are symmetric.

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