الفهرس 
IntroductionOnly 14 pages are availabe for public view
 |  | from | 114 |  |  |
| | | from | 114 | | |
Abstract
The present work represents a theoretical study of the viscous effects in supersonic flow on a flat plate. The viscous effects on both sides of the flat plate, so as the effect of the leading edge shape on the behavior of the shock wavs regarded.
The analysis is based on the solution of the equation of the steady, two dimensional, compressible, laminar boundary layer for perfect gases. It is assumed that the heat generated in the boundary layer by internal friction is no more of secondary importance. The change in the flow parameters occurring due to the shock wave at the points of intersection of two planes has been investigated and considered, during the evaluation of the effect of the independent variables, Mach number, eemi-vertex angle of the leading edge and the angle of attack on the flow parameters.
The results are obtained in the form of graphs linking the viscous effects in supersonic flow with the independent variables of the flat plate.
The constructed computer program used for numerical analysis of the group of equations used in solving this problem leads to the following highlights:
a) Mach number has the major effect on this study.
b) Leading edge angle e and the angle of attack C( have less effect on the local akin friction coeffi -and the achieved wall temperature Tw .
c) The different B.L thicknesses depend mainly upon flow velocities and slightly affected by different leading edge angle and angle of attack.
Moreover, the analysis of the results give a suggestion about the expected type and properties of the material necessary to endure the thermal and shear stresses resulted as effects of supersonic flow on the flat plate.