The state of the art in aerospace engineering has been continually accelerated by the development of advanced analysis and design tools. Used in the early design stages for aircraft and spacecraft, these methods have provided a fundamental understanding of physical phenomena and enabled designers to predict and analyze critical characteristics of new design, including the capability to control or modify unsatisfactory behavior.


Pre-Processing Solutions : 3-D parametric modeling, bi-directional CAD connectivity, geometry creation and editing, structured, unstructured, Hexa Grid generation. Software Facilities: ANSYS ICEM CFD, GAMBIT, ANSYS Design Modeler.

Mechanical Solutions : Static, modal and harmonic analyses; transient analyses; buckling and fatigue analyses; automated contact analyses; composites; deformable geometry; geometric nonlinearity; linear and nonlinear materials; component mode synthesis; rigid and flexible multi-body dynamics; rotordynamics; explicit dynamics; topological optimization; customizable loads, Software Facilities: ANSYS CFX & ANSYS Mechanical.

Thermal Solutions : Steady and unsteady; conduction, convection and radiation; phase change; mass transport; fluid elements; parallelized Software Facilities: ANSYS Mechanical, ANSYS CFX, ANSYS FLUENT,

Fluids Solutions : Application-specific, CAD-embedded and easy-to-use general interfaces; moving and deforming geometry; steady and unsteady flow; 2-D, axi-symmetric, axi-symmetric with swirl and 3-D flow; incompressible and compressible flow; inviscid and viscous flow; laminar, transitional and turbulent flow; aero-acoustics; convective, conductive, radiative and conjugate heat transfer; species transport and reactions; dispersed and mixed phases; combustion; rotating machinery with stage interfaces; customizable physics and user interface; segregated and coupled solvers,; parallelized Software Facilities: ANSYS FLUENT, ANSYS CFX, ANSYS ICEM CFD

Code Development Solutions :

  • Build up of 1 D & 2 D Code for Understanding Flow Physics/Chemistry and preliminary configuration.
  • Development of various CFD models using finite difference & finite volume method. Linear solvers, implicit and explicit methods.
  • Development of Compressible and incompressible solver.

High quality structured mesh

  • Number of elements - 2801397 hexa elements
  • Total number of Nodes - 2732536
  • Triling edge - 8 nodes
  • Wing chord - 40 nodes
  • Wing span - 70 nodes
  • Fuselage length - 178 nodes
  • Fuselage circumference - 44 nodes


Propeller Analysis – RANS Calculation

Computational mesh close to Eppler 387 Aerofoil surface

Static pressure contour at Mach No.0.2 & α = 8O

Pressure coefficient at Mach No. 0.2 & α = 8O

Mach No. contour

3D front view 3 bladed propeller Propller Analysis – RANS Calculation

Magnified view of blade region

Magnified view of blade region

Computational mesh of 3 bladed propeller