1990 Fiscal Year Final Research Report Summary
Research on Design Tool for the Supersonic Intake
| Project/Area Number |
01550050
|
|---|
| Research Category |
Grant-in-Aid for General Scientific Research (C)
|
| Allocation Type | Single-year Grants |
|---|
| Research Field |
Aerospace engineering
|
|---|
| Research Institution | University of Osaka Prefecture |
|---|
Principal Investigator |
NAKAHASHI Kazuhiro Univ. of Osaka Prefecture Associate Prof., 工学部, 助教授 (00207854)
|
|---|
| Project Period (FY) |
1989 – 1990
|
| Keywords | Aero engines / CFD / Shock-Boundary Layer Interaction |
|---|
| Research Abstract |
In the development of the supersonic commercial airplane, the key technology is the supersonic engine whose aerodynamic performance highly depends on the intake. The flow field inside of the intake is complex because of the shock-boundary interactions, and is not only important for the engineering applications but also interesting from the viewpoint of fluid physics.
In the present research, a numerical scheme has been developed for computing intake flow field. The method employed the upwind TVD scheme in order to compute the stiff flow field of the shock-boundary layer interactions. The computed results showed qualitatively good agreements with the experiments. However it is also shown that further investigation is required in turbulence modeling and three-dimensional treatments for quantitatively good agreement.
The application of the computational fluid dynamics to the engineering design tool is also investigated. The main subjects of this are to develop an efficient grid generation scheme and the post-processing of the computational results. These pre- and post-processing are important for the effective use of the CFD in the routine engineering works.
The research will be continued on the three-dimensional flow simulations of the intake flow field. For this purpose, to develop a flow solver utilizing the up-to-date vector and parallel architecture of the supercomputer is essential.
|
