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Flotran: Estimating Drag Coefficient of a Rocket

Flotran: Estimating Drag Coefficient of a Rocket

Flotran: Estimating Drag Coefficient of a Rocket

(OP)
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

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