Airfoil Data
RC10N1
NASA/LANGLEY RC-10(N)1 AIRFOIL
Wing Geometry Simulator
The NASA/LANGLEY RC-10(N)1 AIRFOIL is a thin 6.4% chord-thickness airfoil with a maximum camber of 3.2% at 35% 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 -3.2°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 53 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 RC10N1 appears in the wing design of at least 1 documented aircraft — notably by Sikorsky. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the RC10N1 typically compare it against profiles of similar thickness: BOEING 707 .54 SPAN AIRFOIL, NASA/LANGLEY LS(1)-0013 AIRFOIL, GOE 11K AIRFOIL, E186 (10.27%), NASA/AMES A-01 AIRFOIL. The NASA NLF(1)-0115 is another reference profile frequently considered alongside it.
Aircraft Using the RC10N1 Airfoil
Sikorsky S-61 (Carson/ATI blade) | Sikorsky | NASA RC(4)-12/RC(4)-10 | NASA RC(3)-10 |
Wing lofting: 1 of these aircraft taper from RC10N1 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 RC10N1 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.4%) and max camber (3.2%).