Airfoil Data
VR7
BOEING-VERTOL VR-7 AIRFOIL
Wing Geometry Simulator
The BOEING-VERTOL VR-7 AIRFOIL is a 9.1% chord-thickness airfoil with a maximum camber of 4.6% at 33% 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 -4.6°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 VR7 appears in the wing design of at least 2 documented aircraft, including designs from Bell and Boeing. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the VR7 typically compare it against profiles of similar thickness: BOEING-VERTOL VR-7 AIRFOIL WITH TAB, USA 45 M AIRFOIL, USA 26 AIRFOIL, CLARK V AIRFOIL, FX 83-W-108. The NASA SC(2)-0606 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the VR7 Airfoil
Bell 301 XV-15 (Boeing ATB) | Bell | Boeing V43030-1.58/VR-7 | Boeing VR-8 |
Boeing 301 XCH-62 HLH | Boeing | Boeing V43015/V43012/VR-7 | Boeing VR-8 |
Wing lofting: 2 of these aircraft taper from VR7 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 VR7 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.1%) and max camber (4.6%).