Aerodynamics Simulation
Aerodynamic Simulation is at the core of what our CFD consulting engineers do at our CFD consultancy Singapore office in BroadTech Engineering.
Featured Aerodynamics Simulation Case Studies
Aerodynamic Investigation on a Wing Shaped Deflector (Hydrofoil)
Conducted an aerodynamic study on a newly designed wing shaped deflector used in seismic vessels to find out reasons for an unexpected behavior (yields lift force less than the estimated value).
A CFD design validation study (against an experiment) was conducted by our CFD consultant on the scale down model of existing wing to develop a methodology to perform analysis on a new wing.
Noticed the flow separation on the main plane of the new wing which is considered to be the main reason for the missing lift.
Objective: The computational fluid dynamics simulation objective was to simulate the flow around an airfoil in front of wind tunnel shear layer.
Methodology: 2D RANS simulation based on OpenFoam using steady and unsteady solvers
Outcome: The pressure outcome obtained from the fluid dynamic analysis was generally matching the experimental data
Aerodynamic CFD Design of Turbine Centre Frames (TCF)
Objective: Aerodynamic simulation design of Turbine Centre Frames (TCF) from preliminary to detailed design phases.
Background: This fluid dynamics simulation project used 1D to 2D to 3D design approach and periodic model of the geometry was created from 2D aero design tools. To down select the right design space, various design ideas were generated and then taken through all the design review processes. 3D flow was simulated using CFX and in-house CFD Simulation Software tool for which hexahedral mesh was generated with O-grid using semi-automated meshing technique in ICEM.
The mesh for the fluid flow simulation was targeted to produce y+ of less than 4 in order to accurately capture the boundary layer effects. Pressure inlet and outlet conditions were used and target mass flow was imposed at the exit. Various engine running conditions were simulated including 3D unsteady flow.
The time step was calculated from high-pressure turbine running speed and number of blades both in TCF and upstream turbine. The compressible turbulent flow was simulated using k-omega SST turbulence model.
Results & Conclusion: This computational fluid analysis work led to the successful design of most aggressive TCF ever designed at GE-Aviation and in the world.
Aerodynamic Design Optimization of Shell Eco-Marathon Vehicle
Simulation Objective: The aerodynamic simulation objectives were to identify the design of PEM fuel cell based Shell Eco-marathon vehicle where the aerodynamics of vehicle is important to enhance the performance.
Methodology Adopted: FEM simulation tool of Ansys and Catia were used to simulate the performance of the vehicle and define the geometry.
Outcome: The final model was projected to the fabrication of vehicle. which was participated in the Shell Eco-marathon competition.
Aerodynamics Simulation of Hypersonic Flow Through Thin Plate
Objective: The objective of this CFD simulation project is to satisfy customer request to simulate the effect of air towards the plane wing, similar to these aerodynamic simulation done on vehicle dynamics simulation. The customer has tested it in the lab and get the results but needs us to simulate and obtain the same airflow pattern.
Methodology: The method used for this Computational Fluid Dynamics Analysis is to model simple thin plates with given dimension, specify the Reynold number and velocity.
Outcome Results: The physical time was 10 seconds, and the CFD analysis results for every 0.5 seconds were taken to be tabulated and graphed. The variation of the study was to add shock generator to analyze different flow pattern.
Numerical Investigation of Laminar Flow Over Airfoil with Hemispherical Concavities
Objective:
The golf ball with its surface concavities causes to delay flow separation and in-turn reduces skin friction drag. The aim of the fluid flow analysis is to use surface modifications in form of hemispherical concavities much like the golf ball on the surface of symmetric NACA 0018 airfoil to prolong air cohesion at a high angle of attacks.
Approach/Method:
Flow behavior on an airplane wing which is tilted at 6 degrees to the horizontal. Simple non-viscous model and incompressible approach to model that. Validated the practical example in the book, showing normal shock and isentropic behavior in which stagnation pressure remains same (2nd behavior)
a. The 2-D cad model of NACA 0018 is prepared in CATIA. A hemispherical cavity is CFD modeled at locations varying in {0.02c, 0.05c, 0.07c} of the chord length from the leading edge. b) Re~1000.
b. A highly refined tetrahedral grid was chosen to mesh near the concavities. A total of 50,000 quad elements were used. (Finally, grid independence study showed that this was a highly conservative number).
c. The CFD Flow Analysis simulations for with & without the surface modifications are performed using Ansys FLUENT for laminar flow.
Conclusion
a. The point of flow separation for AOA of 15 degrees was pulled backward from 0.31 (no modification) to 0.37 times the length of the chord. Hence delaying flow separation.
b. Also, the coefficient of drag for airfoil from AOA of 12 degrees onwards showed a drop of 6 %.
Aerodynamic Design Optimization of a Fighter Aircraft Air Intake
Project Objective: Aerodynamic design optimization of an Air Intake of a fighter aircraft.
Methodology: Air intake analysis was carried out using Ansys Fluent, the pressure recovery was plotted vs corrected mass flow rate. suggested different shapes of air intake and duct system within the constraint of other design parameters to increase the pressure recovery.
In addition, a numerical study was also carried out on the ice formation phenomena around the wing for a transient flow. Grid independence analysis was performed in this study and Euler’s multi-phase model has been considered for simulating the problem.
Conclusion: Successfully designed the air intake and duct system with less flow separation to increase the pressure recovery.
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