Airfoil Data
MS313
NASA/LANGLEY MS(1)-0313 AIRFOIL
Wing Geometry Simulator
The NASA/LANGLEY MS(1)-0313 AIRFOIL is a 8.0% chord-thickness airfoil with a maximum camber of 4.0% at 38% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.0°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 58 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 MS313 appears in the wing design of at least 10 documented aircraft, including designs from TL and Aerospool. 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 MS313 typically compare it against profiles of similar thickness: LDS-2 AIRFOIL, S8055 (12%), GOE 396 AIRFOIL, GOE 408 AIRFOIL, GOE 432 AIRFOIL. The GOE 342 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the MS313 Airfoil
Aerospool WT9 Dynamic | Aerospool | NASA MS(1)-0313 | Constant |
Airlony Skylane v.IV | Airlony | NASA MS(1)-0313 | Constant |
Carbon Design FM250 Vampire | Carbon | NASA MS(1)-0313 | Constant |
Flying Machines FM250 Vampire | Flying | NASA MS(1)-0313 | Constant |
GRYF Aircraft MD3 SportRider | GRYF | NASA MS(1)-0313 | Constant |
Lockheed Martin LOCAAS | Lockheed Martin | NASA MS(1)-0313 | Constant |
Orlican M-8 Eagle | Orlican | NASA MS(1)-0313 | Constant |
Rokospol Via | Rokospol | NASA MS(1)-0316 | NASA MS(1)-0313 |
TL Ultralight TL-2000 Sting | TL | NASA MS(1)-0313 | Constant |
TL Ultralight TL-96 Star | TL | NASA MS(1)-0313 | Constant |
Wing lofting: 1 of these aircraft taper from MS313 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 MS313 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.0%) and max camber (4.0%).