> ## Documentation Index > Fetch the complete documentation index at: https://docs.ntop.com/llms.txt > Use this file to discover all available pages before exploring further. # Lesher Teal Hackathon Starter with Quick Aero Estimates > AI context for Lesher Teal Hackathon Starter with Quick Aero Estimates. Not linked in navigation. > This page is for AI assistant context only. To use this package, visit [community.ntop.com](https://community.ntop.com/#/detail/lesher-teal-hackathon-starter). > **Community submission — not verified by nTop.** This package was submitted by an outside community member and has not been reviewed or verified by nTop. Treat its accuracy, safety, and compatibility claims with appropriate caution. ## Summary Parametric Lesher Teal aircraft with a Run Command link to a Python AeroSandbox script that updates cruise CL, CD, L/D and neutral point within seconds of any geometry change. ## Package Details | Field | Value | | - | - | | **ID** | `lesher-teal-hackathon-starter` | | **Type** | Bundle | | **Author** | nTop | | **Version** | 1.0.0 | | **nTop Version** | 6.2+ | | **Domain** | Aerospace | | **Application** | Analysis | | **Complexity** | Intermediate | | **Tags** | `aircraft`, `aerodynamics`, `aerosandbox`, `doe`, `run-command`, `python`, `flow-analysis`, `ai-assisted` | | **License** | MIT | | **Verified** | No | *** A parametric nTop model of the Lesher Teal, the record-setting pusher aircraft that University of Michigan professor Edgar J. Lesher designed and first flew in 1965. It's the starter file for a student hackathon challenge: parameterize the aircraft so it captures the designer's intent, then pull out parameters for a design of experiments. The built-in Aircraft Flow Analysis gives high-fidelity results but takes a while to solve. This package adds a **Quick Aero Estimate** section: an nTop **Run Command** block sends the current geometry to a small Python script, which uses [AeroSandbox](https://github.com/peterdsharpe/AeroSandbox) and reports cruise CL, CD, L/D, max L/D, neutral point and static margin within about 3 seconds of any change. The aero integration (`teal_aero.py` and the Run Command chain) was built with Claude. Lesher Teal model in nTop with flow-analysis streamlines ## Files | File | Purpose | | - | - | | `lesher-teal-hackathon-starter.ntop` | The notebook: wing, fuselage and tail geometry, checks, flow analysis and the Quick Aero Estimate section | | `teal_aero.py` | Quick aero script called by the notebook; also usable from a terminal | | `requirements.txt` | Python dependency (`aerosandbox`) | | `aero-output-example.png` | Example of the plot the script writes | The site's download button gives you the notebook. Get `teal_aero.py` from [this package folder on GitHub](https://github.com/nTopology/Utilities-community/tree/main/packages/matthewmuellernTop/lesher-teal-hackathon-starter), or clone the whole repo: ```bash theme={null} git clone https://github.com/nTopology/Utilities-community.git ``` ## Setup (about 5 minutes) 1. Install Python 3.9 or newer from [python.org](https://www.python.org/downloads/) and tick **Add python.exe to PATH**. 2. Install AeroSandbox: ```bash theme={null} pip install aerosandbox ``` 3. Create the folder `C:\TealAero` and put `teal_aero.py` in it. To use a different folder, change the notebook's **Aero Tool Folder** variable to match, using forward slashes. 4. Check the script works (it prints the baseline estimate): ```bash theme={null} python C:\TealAero\teal_aero.py ``` 5. Open `lesher-teal-hackathon-starter.ntop` in nTop 6.2 or later and save a working copy. 6. The first time the notebook runs, nTop asks you to **Trust** the Run Command block. Click Trust. If AeroSandbox is installed in a different Python (a venv or conda env), set **Python Executable** to that interpreter's full path. ## Using it Every aero-relevant input is a named variable, in the Wings, Fuselage and Stabilizers sections: * **Wing:** root point (its placement), chord, airfoil, span, sweep, taper, twist, dihedral * **H-stab:** the same eight inputs * **Twin fins** (`VStab`): root point, chord, airfoil, height, sweep, taper * **Ventral fin:** root point (`Lower Stab Root`), chord, airfoil, height, sweep, taper * **Fuselage:** the top, side and bottom rail point lists Both the geometry blocks and the aero estimate read these variables. When you replace a typed value with an expression on your own design parameters, the estimate follows automatically. | Direction | Name | Meaning | | - | - | - | | Input | Wing, H-stab, fin, ventral and fuselage variables | Geometry, in model units | | Input | Aircraft Mass | kg (500 = Teal max takeoff weight) | | Input | Cruise Speed (m per s) | m/s (82 = 160 kn) | | Input | CG X | CG location; static margin is measured about it | | Output | Cruise CL, Cruise CD, Cruise L/D | At the cruise mass and speed, sea level | | Output | Max L/D | Best lift-to-drag ratio over angle of attack | | Output | Neutral Point X, Static Margin pct MAC | Pitch stability | | Output | Neutral Point, CG Point | Viewport markers; keep the neutral point behind the CG | Each run also writes `aero_results.json` and `aero_results.png` (polars plus top and side views) next to the script, so you can check the geometry was read correctly. If an estimate doesn't appear, copy the text of **Aero Command Line** into a terminal and run it to see the error. ### From a terminal (DOE) Any key you leave out keeps its Teal baseline value. Lengths are in m, angles in deg. ```bash theme={null} python teal_aero.py wing.span=8 wing.x=2.4 hstab.chord=0.6 mass=520 python teal_aero.py --list ``` `--list` prints every key with its baseline value. Add `--csv doe.csv --no-plot` to each run to collect a sweep into one CSV. ## Evidence and limits * The notebook was prepared and checked in an internal nTop build (43139, with the Notebook API). This publication copy was not reopened in a public nTop 6.2 release. * In that build, Run Command produced the estimate shown above: cruise L/D 14.2, neutral point 2.753 m. Wing-placement and tail changes updated it as expected, and the script matches a direct terminal run. * The flow analysis is included but paused, without results; run it yourself. * This is a quick estimate: * Drag covers only the wing, tails and fuselage. Propeller, cooling, gear and interference drag are left out, so real power is higher. * CL\_max and stall speed are rough. * Moments are untrimmed (no elevator deflection). * A positive twist value is read as washout, and the tip gets half of it because the wing block ramps twist over the full span. * Fuselage sections are modeled as ellipses through the rails. * Use it to rank designs, then check final candidates with the flow analysis. ## License and credits The notebook and script are released under the MIT license; see [LICENSE](LICENSE). * The notebook description embeds the photo [Lesher Teal](https://commons.wikimedia.org/wiki/File:Lesher_Teal.jpg) by FlugKerl2, licensed [CC BY-SA 3.0](https://creativecommons.org/licenses/by-sa/3.0/). That photo isn't covered by the MIT license. * Aircraft dimensions and performance figures are from the [Lesher Teal Wikipedia article](https://en.wikipedia.org/wiki/Lesher_Teal). * [AeroSandbox](https://github.com/peterdsharpe/AeroSandbox) (MIT) is a dependency, not bundled. *** ## Source [https://community.ntop.com/#/detail/lesher-teal-hackathon-starter](https://community.ntop.com/#/detail/lesher-teal-hackathon-starter) ## Download [Download lesher-teal-hackathon-starter.ntop](https://github.com/nTopology/Utilities-community/releases/download/lesher-teal-hackathon-starter-v1.0.0/lesher-teal-hackathon-starter.ntop) This documentation is built and hosted on [Mintlify](https://mintlify.com), a developer documentation platform.