A Flow Analysis of Vectored Thrust Nozzle Using Incompressible Navier-Stokes Solver

비압축성 Navier-Stokes 방정식을 이용한 추력 편향 노즐 해석(원통에서 사각형으로 변환하는 내부 흐름을 중심으로)

Circular-to-rectangular transition ducts are used as exhaust components of high performance fighter aircraft with vectored thrust nozzles. Three-dimensional incompressible Navier-Stokes solver is used to analyze the transition duct. Cross sections of transition duct are defined by superelliptic equation. The grid system is generated by Non-Uniform Rational B-Spline, after generating surface grid by blending the cross sections. Good agreement between the results of the computational simulation and the experimental data is observed.