An Analytical Investigation of Viscous Shock-Layer Flow near the Leading Edge of Slender Bodies under Low-Density Hypersonic Conditions
Final rept. Jul 1969-Jul 1972
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
An analytical investigation and a numerical procedure are presented for calculating the fully viscous shock-layer flow near the sharp leading edge of both two-dimensional and axisymmetric slender bodies uses an implicit finite-difference technique in conjunction with wall slip boundary conditions the shock structure is determined as part of the resulting solution. The mathematical model involves a more complete and accurate set of governing equations and boundary conditions.
- Fluid Mechanics