Recorded airfoil sections
Miles M.68 Boxcar
The UIUC airfoil-usage tables record the Miles M.68 Boxcar with 2 airfoil sections. Each is in the library with its geometry, a stored polar sweep, and DXF and .dat export. The source lists names only — it does not say which station carries which section — so they appear here thickest first.
Sections side by side
| Section | Series | Thickness | at x/c | Camber | at x/c |
|---|---|---|---|---|---|
| NACA 23018 | NACA | 18.0% | 29% | 1.85% | 14% |
| NACA 2412 | NACA | 12.0% | 29% | 2.00% | 42% |
NACA 23018
NACA series · 18.0% thick at 29% chord · 1.85% camber at 14% chord
Also recorded on 97 other aircraft
NACA 2412
NACA series · 12.0% thick at 29% chord · 2.00% camber at 42% chord
wing designs
The sections above are what the source records, not a wing anyone drew. Wings that were drawn — planform, sections and the analysis behind them, all readable — are published under Full-scale aircraft wing designs.
Aircraft-to-section mapping from the UIUC airfoil-usage tables. Section geometry is computed from the library's CST fit; nothing here is a performance claim about the aircraft. All recorded aircraft