Airfoil Data
N0011SC

NACA/LANGLEY SYMMETRICAL, SUPERCRITICAL AIRFOIL

Max Thickness

5.48%

Max Camber

2.74%

0.15 0.05 -0.05 -0.15

0.0 0.2 0.4 0.6 0.8 1.0

Chord (x/c)

Click to expand

Wing Geometry Simulator

Live Geometry

Aspect Ratio 3.33

Area (S) 0.300m²

MAC 0.311m

Taper (λ) 0.50

Params

Span 1.00 m

Root Chord 0.40 m

Tip Chord 0.20 m

Washout 0.0°

Angle of Attack 5.0°

The NACA/LANGLEY SYMMETRICAL, SUPERCRITICAL AIRFOIL is a thin 5.5% chord-thickness airfoil with a maximum camber of 2.7% at 40% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -2.7°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 51 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

The N0011SC appears in the wing design of at least 16 documented aircraft, including designs from EFW and Sikorsky. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the N0011SC typically compare it against profiles of similar thickness: EH 1.0/9.0, GIII BL288 AIRFOIL, EH 2.0/7.0, AG27 Bubble Dancer DLG by Mark Drela | The AG2x airfoils are intended to be used on composite versions of the Bubble Dancer and the Allegro-Lite., GIII BL126 AIRFOIL. The GOE 526 AIRFOIL is another reference profile frequently considered alongside it.

Aircraft Using the N0011SC Airfoil

Aircraft

Manufacturers

Tapered wings

Top manufacturer

EFW

16 aircraft


EFW N-20.01	EFW	NACA 0011-(4.5)(4.5)	NACA 0009-(4.5)(4.5)
EFW N-20.02 Arbalete	EFW	NACA 0011-(4.5)(4.5)	NACA 0009-(4.5)(4.5)
EFW N-20.10 Aiguillon	EFW	NACA 0011-(4.5)(4.5) ?	NACA 0009-(4.5)(4.5) ?
EFW N-20.20 Harpon	EFW	NACA 0011-(4.5)(4.5) ?	NACA 0009-(4.5)(4.5) ?
Lockheed 1649 Starliner	Lockheed	NACA 0015	NACA 0011
Lockheed 200 C-141 Starlifter	Lockheed	NACA 0013 mod	NACA 0011 mod
Lockheed 500 C-5A Galaxy	Lockheed	NACA 0012.41 mod	NACA 0011 mod
Macchi MC.99	Macchi	NACA 0020 ?	NACA 0011 ?
Bell 206 OH-4	Bell	NACA 0011 mod	Constant
Bell 47G-2 H-13G wood blades	Bell	NACA 0017	NACA 0011
Kaman 240 HTK	Kaman	NACA 0012	NACA 0011
Kaman 600 HOK	Kaman	NACA 0012	NACA 0011
Sikorsky S-64 CH-54 Tahre	Sikorsky	NACA 0011 mod	Constant
Sikorsky S-64 Skycrane	Sikorsky	NACA 0011 mod	Constant
Sikorsky S-65 CH-53 Sea Stallion	Sikorsky	NACA 0011 mod	Constant
Sikorsky S-65 HH-53 Super Jolly Green Giant	Sikorsky	NACA 0011 mod	Constant

Wing lofting: 11 of these aircraft taper from N0011SC at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.

Related Airfoils

Engineers evaluating the N0011SC frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.5%) and max camber (2.7%).

Similar by Thickness