Abstract
The effects of static aeroelasticity on the performance of supersonic and hypersonic nozzles are analyzed. Five different configurations of two dimensional converging-diverging supersonic nozzles are investigated. Computational results are validated with experimental data. Two of the configurations, which have the same throat area, throat radius, and convergence angle and total nozzle length, are selected as the baseline geometries. By modifying throat radius and keeping all other geometric parameters to be the same, three more configurations are obtained. Flow analyses are performed by using FLUENT, flow solver software. By considering nozzle walls as flexible structure, a static aeroelastic model is implemented. The flexible wall model uses two dimensional linear beam theory. The results of flexible and rigid walls are compared for hypersonic nozzle cases.
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