It was exhibited at the 1985 RSA meeting at Brienne in France, before it had made its first flight that same year, registered LX-LPW. Flash-3 specification and data follows.
TYPE: Three-seat homebuilt aircraft.
AIRFRAME: Cantilever low-wing monoplane. Entire air-frame constructed of vinylester and resin composites, partially strengthened with carbon fiber. Wings foldable for storage. Wing section at root NACA 43012, at tip 43010. Dihedral 4" 30'. Incidence at root 2" 30', at tip 1". No sweepback. Main spar laminated inside wings. Ailerons and electrically actuated flaps interconnected. Conventional moulded monocoque fuselage, a trapezoidal vertical tail with all-moving tail-plane on top (T-tail), anti-servo tab, fin, and rudder. (Reportedly later a large ventral fin was fitted.)
LANDING GEAR: Electrically and hydraulically retracted tricycle type, with all three wheels size 5.00-5 (40 lb/sq.in, 2.81 kg/sq.cm). Shock absorbers. Mainwheel hydraulic brakes.
POWERPLANT: An 150 hp Avco Lycoming O-320 flat-four engine, driving a Mühlbauer two-blade metal constant-speed propeller with spinner. Other engines of up to 260 hp could be fitted. Fuel capacity: standard tank 69 gal (261 l); long range tank 143 gal (541 l); long range tank with tip tanks 169.3 gal (641 l).
ACCOMMODATION: Pilot and two passengers under large rearward sliding canopy. Baggage capacity 264 lb (120 kg).
AVIONICS: IFR instrumentation plus Micrologic ML 6000 Loran C and radio com standard.
Span over tip tanks: 27 ft 11.75 in (8.53 m)
Span without tip tanks: 26 ft 0.2 in (7.93 m)
Width, wings folded 8 ft 2 in (2.49 m)
Wing aspect ratio without tip tanks: 6.9
Wing chord at root: 4 ft 11 in (1.50 m)
Wing chord at tip: 2 ft 8 in (0.81 m)
Length: 26 ft 0.25 in (7.93 m)
Height: 6 ft 11 in (2.11 m)
Tailplane span: 9 ft 10 in (3.00 m)
Wing area: 107.64 sq.ft (10.00 sq.m)
Wheel track: 4 ft 11 in (1.50 m)
Wheel base: 7 ft 6 in (2.29 m)
Propeller diameter: 6 ft 4 in (1.93 m)
Empty weight: 1,120 lb (508 kg)
Max takeoff weight without tip tanks: 2,196 lb (996 kg)
Max takeoff weight with tip tanks: 2,350 lb (1,066 kg)
Wing loading: 21.83 lb/sq.ft (106.60 kg/sq.m)
Power loading: 15.67 lb/hp (7.11 kg/hp)
Never-exceed speed: 293 mph (472 kmh)
Max level speed at sea level: 227 mph (365 kmh) at sea level
Max cruise speed at sea level: 214 mph (345 kmh)
Econ cruise speed: 207 mph (334 kmh) at 10,000 ft (3,050 m)
Stall speed, flaps down: 50 mph (81 kmh)
Climb: 1,200 ft (366 m)/min
Takeoff run: 755 ft (230 m)
Landing run: 210 ft (689 m)
Service ceiling: 17,820 ft (5,430 m)
Range, standard fuel, two occupants, baggage: 2,045 mls (3,291 km)
Range, max fuel, pilot only: 4,220 mls (6,791 km)
In 1990 Wolff redesigned the aircraft and it reappeared as the Sky-Wolff, offering seating for four adults in the larger fuselage and fitted with an 160 hp Lycoming IO-320 engine. A separate lock-up baggage compartment was provided, and the wings were removable for trailering.
Furthermore it had a modified trailing edge on the vertical tail, a modified undercarriage with trailing link main wheels and sideward opening and shorter nose wheel doors (on the Flash 3 there was a single rearward closing door), a framed canopy and an additional wrap-round window, while overall length was increased to 26 ft 0.2 in (7.93 m).
LX-LPW was first flown in its new form during 1990, and the aircraft was offered as a kit which was intended to be built in the USA by Wolff Aircraft Engineering Ltd. Assembly of the kit aircraft would take the homebuilder approximately 600 working hours. Sadly the prototype was lost in an accident, killing Paul Wolff and all further development was stopped.
Only a few performance data of the Sky-Wolff are known, the cruising speed was 215 mph (346 kmh) and a range of up to 4,200 mls (6,759 km) could be achieved with 169.3 gal (640 l) of fuel.