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CFD (Computational Fluid Dynamics)
& FLIGHT MECHANICS SECTION
- MSES analysis and design code for multi-element airfoil based on Euler equations and boundary layer developed by MIT.
- RAMPANT three-dimensional code based on Navier-Stokes equation with k-ε turbulence model developed by Fluent Inc.
- CODA2D geometrical and aerodynamic design and flow analysis of multi-element airfoils (solver based on boundary element method), developed by Institute of Aviation.
- CODA3D package containing three elements: pre-processor for description of 3D complex geometry using NURBS curves and surfaces, steady/unsteady solver based on the boundary element method, and simple postprocessor for flowfield analysis, developed by Institute of Aviation.
- OVER3D analysis of steady or unsteady flowfield based on numerical solution of the Euler equation moving block structured or overlapping meshes (joint development with Warsaw Technical University), supplemented with the pre-processor from CODA3D and simple grid generator using NURBS.
- OASS transonic wing analysis code based on small perturbation equations developed by Institute of Aviation.
- HCZMAX airfoil analysis code with flow separation effects developed by Institute of Aviation.
- H modified BGK two dimensional, transonic analysis code based on full potential equation with boundary layer.
- VORTR fast vortex lattice method 3D code for multi-surface configuration.
- STB aircraft dynamics and static stability analysis in subsonic flow, developed by Warsaw Technical University.
- DERIV calculation of aircraft stability derivatives, based on panel method, developed by Institute of Aviation.
- SIMUL simulation of aircraft's motion with the application of unsteady aerodynamics based on panel method (developed by Institute of Aviation).
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