Flotran: Estimating Drag Coefficient of a Rocket

[aristox]

Hi,
Im new to Ansys and to the subject of CFD. I waould appreciate any help in a problem im trying to solve in Ansys, which is a small part of my final year project dealing with the design of a small rocket.
I want to perform a simulation of the rocket in flight in air uptil 2500m above MSL, SOLELY for the purpose of estimating the Drag coefficient of the entire rocket (contributed by Nose, Body & Fin interference). I know the the following should be the input parameters:
Nose Cone
- Length
- Diameter
- Profile/Shape

Body/Fuselage (Without Transitions)
- Lenght
- Diameter
- Surface Roughness Height

Fins
- No. of Fins
- Length of Fin Sides(4)
- Fin Thickness
- Thickness at Front Edge
- Profile

Launch Lugs
- No. of Lugs
- Height, Width, Length, Thickness

Other Conditions
- Lower & Upper Mach nos
- Altitude

TO DETERMINE Cd of
Entire Rocket
Body Skin Friction
Nose Pressure Drag
Base Drag
Body Pressure Drag
Fin Pressure Drag
Interference Drag
Fin Skin Friction


I hope to receive your kind help.
Thanx.
Aristo