Three-Dimensional Turbulent Boundary Layer on a Spinning Cone at Angle of Attack.
Final rept. 1 Jun 74-30 Jun 77,
NORTH CAROLINA STATE UNIV RALEIGH DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
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This report investigates the three-dimensional turbulent boundary layer on a spinning cone at small angles of attack in incompressible flow. It is assumed that the boundary layer has no effect on the inviscid flow and thus the inviscid flow is used as the outer boundary condition for the boundary layer equations. A momentum integral technique was used to reduce the governing equations to two. The two resulting partial differential equations were then solved by an implicit finite-difference technique of the marching type. The numerical method developed here gives results which follow the trend of available experimental data and other analytical results. This method was also found to be stable and accurate and fairly insensitive to the step size used in the finite-difference method. Computer solution could be found in the cases where spin rate produces surface velocity at the base of the cone less than the free stream velocity. Test cases were run with a free stream velocity of 60.96 meters per second with a cone half angle of 10 degrees. Angle of attack was either zero or five degrees with spin rates of 0, 400, and 500 revolutions per minute. Typical execution times was less than three minutes on an IBM 370165 computer. Author
- Fluid Mechanics