Compressible

Find projects using the compressible analysis type here. | Page 119

In this simulation, it is aimed to calculate the drag coefficient of an experimental rocket. Although the rocket geometry used is representative, the drag coefficient can be calculated for realistic models by following the simulation steps. K-w SST turbulence model was used for simulation. For the experimental rocket, the speed was taken 270 m / s and a ninety-degree (not realistic) flight angle assumption was made.

Pressure Drop sisi Shell Heat Exchanger Shell and Tube

You have to simulate the flow around a rocket at AoA 0, Mach 0.35, altitude 0 slm, ISA atmosphere

This would be a CFD analysis of asymmetrical airfoil in a virtual wind tunnel

This project involves meshing externally a Boeing 777-200 LR Aircraft, and then simulating its' operation on flight facing an airflow with an axial velocity of 50 m/s.  It is one of the longest-range commercial airliners, with an exterior length and wingspan reaching 63.70 and 64.80 meters respectively.  For this case a model with removed engines was chosen in order to assist convergence and meshing. Also a Symmetry plane was added midst the Part, and half the part was used for meshing and simulation for simplification.  A steady state compressible flow simulation is executed to visualize the air flow around the bodywork and wings of the aircraft, as well as the pressure distribution while on flight.

You have to simulate the flow around a rocket (.STEP file attached) at AoA equal  0, Mach  0.35, Altitude  0 s.l.m., ISA atmosphere.

Compressible | SimScale Project Library | Page 119