The main objective of the PAW-6 nozzle test case is to assess the accuracy of existing computer codes and modeling techniques for simulating the aerodynamics and thermodynamics of jet plumes from axisymmetric supersonic nozzles. The PAW-6 nozzle test cases considers three supersonic axisymmetric nozzle configurations, each with the same exit area, with different internal convergent-divergent (C-D) nozzle contours, for a series of flow conditions where the jet pressure ratio (which prescribes a desired Mach number) and jet temperature are varied. The focus of the nozzle test case will be on predicting the plume development and plume turbulent statistics. The PAW-6 nozzle files including the participant document describing the test cases, computational grids, nozzle geometries, and submission files can be downloaded using the link below.
AIAA Propulsion Aerodynamics Workshop
Sponsored by the Inlets, Nozzles & Propulsion Systems Integration Technical Committee and Air Breathing Propulsion Group
