Abstract
Rocket nozzles accelerate combustion products or high-pressure gases to supersonic velocities. The planar nozzle is a type of conical nozzle, having a rectangular cross section. At low altitude, the ambient pressure is higher than the exiting jet pressure which leads to flow separation from the nozzle wall. In planar nozzles, asymmetric flow separation can be observed at low nozzle pressure ratios. Asymmetric flow separation can lead to undesirable side forces. In the present study, numerical analysis is performed on the flow-through planar nozzles. Nozzle geometries with different divergence angles and same area ratio are considered, and flow analysis is performed using commercial software ANSYS Fluent. All geometries are studied with similar boundary conditions. The numerical analysis is done on 2-D planar models. Reynolds-averaged Navier–Stokes equations are solved with realizable k-e turbulence model. For the validation of the planar nozzle, flow features and wall pressure along the length of the nozzle are taken for different nozzle pressure ratios (NPRs) for 5.7° planar nozzle. It is found that as divergence angle increases magnitude of side load decreases and flow becomes symmetry at low NPR.
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