Numerical simulation of flight body circumference flow
Abstract
Large scale numerical calculations have become possible through the introduction of a numerical simulator. A calculation which beforehand would have taken a month or so to obtain the results now can be done in less than an hour. The quality of research in this field depends greatly on the performance of the computer used. In the numerical simulator, a calculation is possible using about 1.5 million grid points for a three dimensional flow. A calculation grid was sought by the method of solving a three dimensional hyperbolic differential equation. If the physical body surface coordinates are assigned by a hyperbolic type grid formation method, the coordinates of the outside are automatically determined by designating the volume forming the base and orthography of the coordinate lines and a excellent grid mesh can be formed comparatively easily for a convex body. Improvement was made to form a nonintersecting grid for a intermixed concavoconvex physical body shape, and the difficulties in a hyprebolic grid formation were overcome. An example of a calculated grid obtained by applying this improved method to the complete NASA shuttle is given.
 Publication:

JPRS Report: Science and Technology. Japan
 Pub Date:
 October 1987
 Bibcode:
 1987rstj.rept...62.
 Keywords:

 Aircraft Structures;
 Circumferences;
 Computerized Simulation;
 Flow Distribution;
 Three Dimensional Flow;
 Computational Fluid Dynamics;
 Computational Grids;
 Differential Equations;
 Turbulent Flow;
 Fluid Mechanics and Heat Transfer