Calculation of Subsonic Normal Force and Centre of Pressure Position of Bodies of Revolution using a Slender Body Theory - Boundary Layer Method.
WEAPONS SYSTEMS RESEARCH LAB ADELAIDE (AUSTRALIA)
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The aim of this report is to present a method of predicting the aerodynamic characteristics of slender bodies of revolution at small incidence, under flow conditions such that the boundary layer is turbulent. Firstly, a panel method based on slender body theory is developed and used to calculate the surface velocity distribution on the body at zero incidence. Secondly this velocity distribution is used in conjunction with an existing boundary layer estimation method to calculate the growth of boundary layer displacement thickness which is added to the body to produce the effective aerodynamic profile. Finally, recourse is again made to slender body theory to calculate the normal force curve slope and centre of pressure position of the effective aerodynamic profile. Comparisons made between predictions and experiment for a number of slender bodies extending from highly boattailed configurations to ogive-cylinders, and covering a large range of boundary layer growth rates, indicate that the method is useful for missile design purposes. Author
- Fluid Mechanics