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FEA for JETcentral · 0.1.0

FEA for JETcentral

Save Results from Lattice-Boltzman method and use them here

Ordinary Wing Box / Tail Box loading

WING BOX → NASTRAN

Prepare and evaluate Wing Box, H Tail Box and V Tail Box designs with beam and shell models.

MSC Nastran 2021.1

Windows 64-bit · 2.26 GB · license required

Download installerInstall guide
Wing Box design not checked yet.

Open this page using FEA for JETcentral at the top of Wing Box, H Tail Box or V Tail Box.

Analysis setup

Linear static · SOL 101 · right exposed wing

Subtract the mesh’s structural weight × load factor from lift. Fuel, control-surface and system mass relief are excluded.

Coarse uses 12 background chord/span divisions; Medium 24; Fine 48. Ribs, holes, spars and stiffeners are retained. Compare finer meshes before relying on peak stresses.

Positive torque acts about aircraft +Y. Applied equally in both subcases.

Builds the input file from this design snapshot. Save the prepared .bdf file using the adjacent Save button.

Load cases

Aerodynamic lift acts at the local quarter chord, with moments transferred to the connected skin nodes. Root nodes are fixed in all six degrees of freedom.

Exposed Wing Box

Blue: skin · orange: spar webs · green: ribs · purple: spar caps · red: stiffeners. Drag to rotate, right-drag to pan, wheel to zoom.

Model details

Actual shell thickness and beam cross-sections are shown at 1:1 scale; zoom in to inspect thin walls. Mesh edges follow the exported elements. Display volumes do not add solid elements to the NASTRAN model.

Design coverage and assumptions

Mesh placement follows ribs, spars, stiffener paths, section transitions and spar terminations, with 32 boundary points per rib hole. The baseline span/chord sampling is regular; no stress-driven adaptive refinement or convergence study has been performed.

  • No design snapshot loaded.

Based on the beam/shell modeling approach in Clark Briggs’s FEA4JET July 23, 2026 distribution. This page reads JETcentral’s Wing Box design directly; it does not require a CPACS conversion.

Preparing the model creates an input file. The evaluation buttons run separate beam or CalculiX shell calculations. Review diagnostics and equilibrium, and check mesh convergence before interpreting stresses.

Use CFD Pressures

Integrate a saved pressure map into vertical forces and pitching moments for the right exposed wing. This replaces the ordinary aerodynamic load cases until you choose Undo CFD Pressures.

The saved Cp and freestream dynamic pressure set the loads. The multiplier and safety factor each apply once. The flight load factor affects only the existing optional structural inertia relief. A negative multiplier reverses the saved loads; it does not calculate a new aerodynamic condition.

Pressure samples are an instantaneous near-wall voxel approximation. This transfer captures vertical bending and pressure-induced torsion; in-plane forces and local skin-pressure stresses are omitted. Review the geometry, coverage and CFD convergence.