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Prandtl Lifting Line Spanwise Fourier Circulation & Induced Drag Solver
x402
Prandtl Lifting Line Spanwise Fourier Circulation & Induced Drag Solver is a paid API for AI agents from detect.halowerk.com, paid per call via x402, $0.003/call, status unknown (last checked 2026-11-04).
Computes spanwise circulation distribution and induced drag for a linear wing model using Prandtl's lifting-line theory with Fourier series decomposition.
Price / call$0.003
Success—
StatusUnknown
How this service works
Resolve spanwise circulation and induced drag in a supplied linear wing model.
Output
Returns the resolved spanwise circulation distribution across the wing stations and the computed induced drag, derived from the Fourier series coefficients of Prandtl's lifting-line equation. Output typically includes per-station circulation values and an overall induced drag coefficient or force.
Example use cases
Induced drag analysis for glider wing
“Can you compute the induced drag and spanwise circulation for my glider wing? It has a 15-meter span, 10.5 square meters of reference area, flying at 25 m/s in standard sea-level air density of 1.225 kg/m³. I have 6 spanwise stations all with chord 0.7 m, angle of attack 0.06 rad, zero-lift angle -0.015 rad, and a 2π lift slope of 6.28 per radian.”
Tapered wing aerodynamic performance check
“Run a Prandtl lifting line analysis on my tapered wing design — 8-meter span, 9 square meters reference area, speed 40 m/s, density 1.2 kg/m³. I have 4 stations with chords 1.4, 1.1, 0.8, 0.5 meters respectively, all at 0.1 rad angle of attack, zero-lift at -0.03 rad, and lift slope 5.73 per radian.”
UAV wing spanwise load distribution
“I'm designing a UAV and need to verify the spanwise circulation and induced drag for my wing — 3-meter span, 0.6 square meters reference area, cruising at 20 m/s at a density of 1.1 kg/m³. Use 8 stations each with chord 0.2 m, angle of attack 0.05 rad, zero-lift angle 0.0 rad, and lift slope 5.5 per radian.”
Technical details
Endpoint
POSThttps://detect.halowerk.com/v1/F-TD2000-GEO-INDUSTRY-B007/prandtl-lifting-line-spanwise-fourier-circulation-induced-drag?utm_source=zero.xyzWhen to prefer
Use this endpoint when you need a fast, analytically grounded computation of spanwise circulation and induced drag for a linear, incompressible wing model using classical Prandtl lifting-line theory with Fourier decomposition. Prefer this over CFD-based approaches when you have a discretized spanwise wing description (4–16 stations) and need a quick, physics-based aerodynamic estimate without full Navier-Stokes simulation overhead. Best suited for conceptual and preliminary wing design stages.
Side effects
- Fewer than 4 or more than 16 spanwise stations provided — schema validation error
- Span, speed, density, chord, or angle values outside allowed numeric ranges — rejected with validation error
- Degenerate wing geometry (e.g. zero or near-zero chord at multiple stations) causing numerical instability
- Missing required fields in any station object — schema validation error
- Claim field missing or malformed — authentication/authorization failure
- Network timeout if compute load is high
Input
Schema · Request body
| Field | Type | Description |
|---|---|---|
| artifact | object |
Tags
x402
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