SU2 CFD — JETcentral

Aircraft / wall pressure

Open from JETcentral or load an aircraft JSON.

1. Aircraft

Load aircraft JSONLoad rebuilt SU2 surface

Rebuilt surfaces must match this aircraft. Their measured approximation is shown after loading; they replace the analysis mesh only.

Reload saved SU2 pressure results

2. Conditions

MachAltitude (ft) Alpha (deg)Beta (deg) Reference area (ft²)Reference chord (ft) Moment X aft (ft)Moment Y right (ft)Moment Z up (ft)

3. Mesh and solver

Solver

Spatial accuracyNear-body volume size (ft)Far-field half-width (aircraft lengths) Maximum iterationsCFLDensity residual target (log10)

First order is more diffusive; compare against second order and finer meshes. Default CAD sliver cleanup uses 0.01 inch. An imported rebuilt surface uses its reported sampled deviation instead. The selected wall triangles are retained during volume meshing. Mesh size controls the surrounding tetrahedra. Compare mesh resolutions and far-field sizes before relying on results. Euler does not model skin friction, boundary layers, or stall; engine ducts have no powered flow.

4. Calculate

Run location

5. Local helper and model scope

Install SU2 8.5.0, Gmsh 4.15.2, NumPy and SciPy. Run the helper with your native SU2_CFD executable:

This page uses genuine SU2 calculations on a closed aircraft surface. The first integration supports compressible Euler, Mach 0.05–2.0. RANS requires a separate boundary-layer meshing workflow.

SU2 documentation

Aircraft / wall pressure

SU2 results