Abstract
A CFD-based design system, CASPER (Computational Aerodynamics System for Performance Evaluation and Research), was developed at TRDI-JDA for advanced aircraft design at the next generation. In this paper, hybrid unstructured Reynolds-Averaged Navier-Stokes computations around a military aircraft, F-16 A, powered configurations including inlet airflow and jet exhaust effects of propulsion system were carried out as a practical example by using the CASPER. In order to validate the present CFD code, the present computed results are well compared to the wind-tunnel testing data with respect to total pressure recovery ratio on engine compressor face and aft-body pressure distributions at steady state. Thus, the present hybrid unstructured Navier-Stokes code is expected to be effective as one of design tools of advanced aircraft propulsion system.
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