권오준 교수

U.S. Army Research Office as part of the Center of Excellence in Rotary Wing Aircraft Technology, contranct numbers DAAG29-82-K-0094 and DAAL3-88-C-0003, monitored by Dr. Robert Singlcton.

The sectional and total aerodynamics load characteristics of moderate aspect ratio wings with and without simulated glaze leading-edge ice are studied using a three-dimensional, compressible Navier-Stokes solver. The wing has an untwisted, untapered planform shape with NACA 0012 airfoil section. The aspect ratio of the wing is chosen to be 5. Comparisons of computed surface pressures and sectional loads with experimental data for identical configurations are given. The abrupt decrease in the win

An unstructured dynamic mesh adaptation and load balancing algorithm has been developed for the efficient simulation of three-dimensional unsteady inviscid flows on parallel machines. The numerical scheme was based on a cell-centred finite-volume method and the Roe's flux-difference splitting. Second-order accuracy was achieved in time by using an implicit Jacobi/Gauss–Seidel iteration. The resolution of time-dependent solutions was enhanced by adopting an h-refinement/coarsening algorithm. Para

Temperature determination in a shock tube is one of the most important factors to understand the relevant flow physics inside. In the present study, the reservoir temperature determination in a shock tube using the ultraviolet emission spectra of hydroxyl radical (OH) A-X band was carried out. A radiation model for the OH A-X transition was developed, and it was validated using the benchmark data. Curve fit parameters, such as a peak-to-peak ratio and the absolute peak intensity of the P-branch,

A three-dimensional Navier-Stokes flow solver is developed on unstructured tetrahedral meshes. For a turbulence closure, a standard high-Reynolds-number k-e model with a wall function boundary condition is used. The seven equations of motion are discretized and integrated in a tightly coupled manner. The time integration is achieved using an explicit Runge-Kutta time-stepping scheme. The inviscid flux terms are discretized based on a cell-centered finite volume formulation with Roe's flux-differ