THE LAMINAR BOUNDARY LAYER ON A CONE IN A SUPERSONIC AIR STREAM AT ZERO ANGLE OF ATTACK
RAND CORP SANTA MONICA CA
Pagination or Media Count:
This report demonstrates that the integration of the equations for the laminar boundary layer on a cone in a supersonic air stream can be reduced to the equations for the flat plate. The simple result is obtained, that on the cone the boundary layer is different by 1square root of 3 as compared to the plate. The mean friction coefficient and the heat transfer coefficient are greater by the factor 23 times the square root of 3.
- Numerical Mathematics