The generic customization framework is put to use for rapid design evaluation of missiles & rockets. Over a period of time, three different variants have been delivered.

Missile and Rocket configuration variant 1 (Spinning Missile)

Missile and Rocket configuration variant 2 (Free Rolling Tail)

Missile and Rocket configuration variant 3 (Control Surface Deflection)

The evolution of features through the variant deployment cycle is listed below:

Feature Definition	First Variant	Second Variant	Third Variant
Projectile Type	Spinning Missile	Free Rolling Tail (FRT)	Control Surface Deflections
Main Cylinder Body	Length & Diameter	Length & Diameter	Length & Diameter
Cylinder Features	Max. 9 steps of user defined heights & respective location	Any number of coupler / cylinder combination	Any number of coupler / cylinder combination
Nose Type	Selection from 7 types & associated geometrical parameters	Selection from 7 types & associated geometrical parameters	Selection from 7 types & associated geometrical parameters
Tail Fin Type (No. of Geometrical Parameters)	Wrap Around Fin (15)	Free Rolling Tail with Rotating Reference Frame zones around it (15)	Non-Rolling Fin (16)
Max. Cant Angle	1 Degree	1 Degree	15 Degrees
Canard
Max. Canard Deflection	-NA-	15 Degrees	15 Degrees
Control Surface Wing
Max. Wing Deflection	-NA-	-NA-	10 Degrees
Canard - Fin Orientation	-NA-	Only Inline	Inline or Cross
Simulation Type	Euler	RANS with Multiple Reference Frame	RANS
Simulation Manager	Single Job Submission	Single Job Submission	Multiple Job Submission
Data Utility	Trajectory Prediction	Control using Canard Deflections	Multiple Control Surface Evaluation