The GFS-UAV project

A Coanda effect flying saucer
created on March 10, 2006 - JLN Labs - February 25, 2007
Toutes les informations et schémas sont publiés gratuitement ( opensource ) et sont destinés à un usage personnel et non commercial
All informations and diagrams are published freely (opensource) and are intended for a private use and a non commercial use.

The GFS-UAV, propelled by an electric engine, uses the Coanda effect to take off vertically, fly, hover and land vertically ( VTOL ). There is no big rotor like on an helicopter and the flight is very stable and safe for the surrounding. The design of the GFS-UAV N-01A is based on the Geoff Hatton' flying saucer from GFS Project limited.

Le GFS-UAV, propulsé par un moteur électrique, utilise l'effet Coanda pour décoller verticalement, voler, faire du stationnaire et atterrir verticalement ( VTOL ). Il n'y a pas un grand rotor comme sur un hélicoptère et le vol est très stable et sûr pour l'environnement. Le model du GFS-UAV N-01A est basé sur la soucoupe volante de Geoff Hatton de GFS Project limited.

Dec 19, 2006 : The BIG Coanda Saucer N02 has done successfuly its 1st flight

If the video doesn't start itself, click on the "Refresh" button on your internet browser

BONUS : The GFS-UAV N01 for the FMS flight simulator

Dec 19, 2006 : FIRST FLIGHT of the BIG Coanda Saucer N02

Manoeuvrability and translation test flights at HIGH SPEED

Outdoor test flights with a wind speed up to 10 km/h

New improvements of the model N-01A (Woow...)

Successful hovering at 3 meters above the ground

The GFS-UAV in action with a video-camera

Photos and a video of the outdoor test flights

Tests flights videos on AFPD and genesis of the project

The GFS-UAV N-01A : Full plan and construction details

The Coanda Effect Test Bench ( CETB )

The N-XX an EHD Coanda Effect craft

The big UAV N-02 construction details


Documents, links and references :

PATENTS from GFS Projects Ltd :

Abstract of GB2424400
To prevent the spin of a craft designed to move though, or on a surface of a fluid, means are provided to vary the effective surface area of an aerofoil 6. The craft may be of the type in which a fan 2 directs fluid over a dome-shaped canopy 1 utilising the Coanda effect to generate lift, a plurality of aerofoils 6 being used to counter unwanted rotation of the canopy caused by a reaction to the rotation of the fan. Each aerofoil 6 may be driven into or out of a respective slot by means of an actuator controlled by a signal generated in response to comparison of an output signal, produced by an optical or piezoelectric gyroscope, with a desired attitude set by a steering mechanism. The aerofoils 6 may be located where the angle of attack in relation to the airfiows 7, 14 produced by the fan 2 is significantly dependent upon fan speed.
Abstract of GB2424405
In a craft having a rotor 9A, 9B, 9C producing a flow over an aerodynamic (eg. domed) surface 1, to create lift or thrust, the gyroscopic effect of the rotor, when driven at full power, is such as to give the craft positive stability. The rotor may comprise part of a radial flow fan 2, having blades 9C, and a heavy annular magnet 9B cooperating with fixed coils 7A for effecting drive of the rotor. The resulting angular momentum of the rotor may afford gyroscopic stability enabling the craft to hover close to the ground or a vertical surface. Pitch and roll control may be achieved by vanes PV1, PV2, RV1, RV2 controlled electronically in response to rotation sensed by optical gyroscopes S1, S2 and taking gyroscopic precession into account.
Abstract of GB2424406
A thrust generation arrangement comprises means 3 to causes fluid to flow over a surface 1 of double convex curvature, the surface 1 causing the fluid to divert from a radial flow towards an axial direction by the Coanda effect. The radius of curvature of the surface 1 decreases progressively less rapidly in a downstream direction. The arrangement may be used to propel a vertical take-off aircraft, the fluid may be caused to flow by a radial fan 3, and the surface 1 may be dome shaped.
Abstract of GB2424463
A vehicle, preferably an aircraft, comprises an impeller (3, fig 2) which in use causes fluid to flow over a surface 1 of the vehicle and produce lift or thrust via the Coanda effect. An intervention mechanism 7 is used to energise a boundary layer 10 of the fluid on the vehicle surface 1 so as to control the point at which separation of the boundary layer 10 from the vehicle surface 1 occurs. The intervention mechanism 7 can thereby operate to control the steering of the vehicle. The intervention mechanism may comprise a vibrating diaphragm 8 and/or a flow of fluid though an opening 6 on the vehicle surface, or a vortex generator.

For more informations, please contact Jean-Louis Naudin :

return to the UAV home page

website statistics
visitors since March 10, 2006