COMPUTATIONS of transonic flows over a practical wing shape are carried out using three-dimensional Reynolds-averaged “thin-layer” Navier-Stokes equations. Computations are done for several angles of attack and the results reveal the flow pattern for each case. The comparison of the computed surface pressure with the experiment shows good agreement. This indicates the importance of the Navier-Stokes computations. The computation which uses about 200,000 grid points for each case requires about 1.5 h on a Japanese supercomputer.
|Number of pages||2|
|Publication status||Published - 1987 Mar|
ASJC Scopus subject areas
- Aerospace Engineering