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20 October, 2008
New customized package for aerodynamic calculations on missiles & rockets
Zeus Numerix rolls out the third variant of its customized package for aerodynamic calculations on missiles & rockets for DRDO laboratory. A product from its Center of Excellence (CoE) for Customization, it would help our clients to rapidly ascertain impact of design changes for missile configurations. Usage of automated structured (100% Hexa) meshing and ease of obtaining solution over the entire flight envelope ensures availability of reliable quality data during initial design stages.

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
Missile and Rocket configuration variant 1 (Spinning Missile)
Missile and Rocket configuration variant 2
Missile and Rocket configuration variant 2 (Free Rolling Tail)
Missile and Rocket configuration variant 3
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 Red Cross Green Check Green Check
Max. Canard Deflection -NA- 15 Degrees 15 Degrees
Control Surface Wing Red Cross Red Cross Green Check
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


ZNTutor-CFD