Airfoil Data
RAF31
RAF 31 AIRFOIL
Wing Geometry Simulator
The RAF 31 AIRFOIL is a 8.1% chord-thickness airfoil with a maximum camber of 4.1% at 40% 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 -4.1°.
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 RAF31 appears in the wing design of at least 5 documented aircraft, including designs from Bristol and Cranwell. 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 RAF31 typically compare it against profiles of similar thickness: GOE 335 (D.F.W.) AIRFOIL, BE50 (original), DEFIANT CANARD BL145 AIRFOIL, GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL, GOE 144 (MVA H.21) AIRFOIL. The NACA M22 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the RAF31 Airfoil
Bristol 96 Fighter IV | Bristol | RAF-31 | Constant |
Cranwell CLA 4 | Cranwell | RAF-31 mod | Constant |
Handley Page HP.32 Hamlet | Handley | RAF-31 | Constant |
Parnall Peto | Parnall | RAF-31 | Constant |
Villier V-24 | Villier | RAF-31 | Constant |
Related Airfoils
Engineers evaluating the RAF31 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.1%) and max camber (4.1%).