Airfoil Data
SSCA09
SIKORSKY SSC-A09 AIRFOIL
Wing Geometry Simulator
The SIKORSKY SSC-A09 AIRFOIL is a thin 5.6% chord-thickness airfoil with a maximum camber of 2.8% at 34% 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 -2.8°.
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 SSCA09 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 SSCA09 typically compare it against profiles of similar thickness: SIKORSKY SC1095 AIRFOIL, AG54, NACA 64-209, NLR-1T AIRFOIL, RAF 15 AIRFOIL. The Curtis C-72 is another reference profile frequently considered alongside it.
Aircraft Using the SSCA09 Airfoil
Sikorsky X2 | Sikorsky | Sikorsky DBLN526/SC325218/SC36212 | Sikorsky SC36210/SSC-A09 |
Wing lofting: 1 of these aircraft taper from SSCA09 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 SSCA09 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.6%) and max camber (2.8%).