Abstract
This paper describes the aerodynamic assessment of a particular variable area fan nozzle (VAFN) concept. This concept offers a variation in the fan nozzle throat area by displacing the inner fairing structure (IFS), which is also known as the core fairing structure. A few different design configurations were developed through the variation in the design parameters. The aim of the assessment was to perform a comparative aerodynamic study by evaluating the main performance parameters such as the nozzle thrust coefficient, nozzle discharge coefficient and the after-body drag at different flight conditions. The required boundary conditions and the magnitudes of the variation in the nozzle throat area were defined following the performance calculations of the whole engine.
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