Single Panel Wing

This page is for AI assistant context only. To use this package, visit community.ntop.com.

Summary

Create a Single Panel Wing driven by Root Chord Length, Wing Span, QC Angle, and Taper Ratio.

Create a Single Panel Wing driven by Root Chord Length, Wing Span, QC Angle, and Taper Ratio.

Clone this repo or copy the package folder into your nTop workspace:

git clone https://github.com/nTopology/Utilities.git

The package lives at packages/ntop/single-panel-wing/.

Open the provided .ntop file in nTop 5.45+.
Add the Single Panel Wing custom block in your notebook.
Define the Root Point to position the wing relative to your fuselage.
Adjust the Quarter Chord Angle and Dihedral Angle to set the wing’s orientation and stability characteristics.
Control the wing’s shape using Root Chord Length, Wing Span, and Taper Ratio.
Apply aerodynamic washout by adjusting the Twist Mag.
The output is a mirrored Implicit Body, providing a full wing assembly symmetrical across the global plane.

Name	Type	Description
`Root Point`	Point	The frontmost point where the wing attaches to the fuselage.
`Root Chord Length`	Scalar	Wing length from front to back at the root.
`Wing Span`	Scalar	Full span of both wings (tip-to-tip).
`Quarter Chord Angle`	Scalar	Sweep angle measured at 25% chord line; positive values sweep back, negative sweep forward.
`Taper Ratio`	Scalar	Ratio of tip chord to root chord (defines how much the wing narrows).
`Twist Mag`	Scalar	The magnitude of angular twist (washout) from root to tip.
`Dihedral Angle`	Scalar	The upward V-angle of the wings for lateral stability.
Output	Implicit Body	The final generated, twisted, and mirrored wing geometry.

MIT.