12/31/2013. Remarks by Johan Visschedijk: "Donald S. Wolf of Huntington, New York, USA, designed and built a diminutive sporting biplane known as the W-11 Boredom Fighter, styled to represent a single-seat biplane fighter of WW I vintage. Although based on no single aircraft, it was said to be fairly simple to construct, using a minimum of special tools. It was capable of accommodating a pilot up to 6 ft 1 in (1.85 m) tall and weighing up to 200 lb (91 kg), was intended primarily for sport flying and was not fully aerobatic. Power plant could vary between 50-100 hp, but a 65 hp Continental A65 engine was recommended.

Design of the Boredom Fighter began in July 1976 and construction of the prototype started in August 1977. The first flight was achieved on August 30, 1979. Plans were available to amateur constructors and about thirty have been registered. The pictured aircraft was built by Peter J.D. Gronow, Carmarthen, Wales, UK, in 1986. In 2003 the aircraft was registered to Christopher M. Bunn, Pen-Y-Fai, Wales."

Wings: Braced single-bay biplane, with I-type interplane struts and N-type cabane struts. Wing section NACA 4412. Dihedral 1° on all wings. Incidence 0° on upper wing, 1° 30' on lower wings. No sweepback. Wooden structure, with solid spruce spars and truss ribs, fabric covered. Constant chord ailerons on lower wings, of similar construction to wings. No flaps.
Fuselage: Spruce Warren truss structure, with mahogany plywood covering in cockpit area; fabric covered rear fuselage.
Tail unit: Wire-braced spruce structure, fabric covered, comprising conventional tail plane and elevators, rounded fin and rudder. Bungee trim on elevators.
Landing gear: Non-retractable tail wheel type. Two side V-struts and half-axles. Rubber bungee shock-absorption. Shinn main wheels, size 6.00-6, with Goodyear tires. Wolf tail wheel and tire. Shinn cable-operated brakes.
Power plant: One 65 hp Continental A65 engine recommended, driving a Lewis 43 x 72 two-blade fixed-pitch wooden propeller. One fuel tank in fuselage, capacity 15 gal (56.8 l). Refueling point in top of fuselage. Oil capacity 1 gal (3.8 l).
Accommodation: Pilot only, in open cockpit. Foot heater. Baggage space aft of seat, capacity 8 lb (3.6 kg).

Span, both: 20 ft 0 in (6.10 m)
Wing aspect ratio: 8:1
Wing chord, constant: 2 ft 6 in (0.76 m)
Length: 15 ft 8.5 in (4.79 m)
Height: 6 ft 0 in (1.83 m)
Tail plane span: 6 ft 4 in (1.93 m)
Wing area: 97.5 sq.ft (9.06 sq.m)
Wheel track: 5 ft 0 in (1.52 m)
Wheel base: 12 ft 0 in (3.66 m)
Propeller diameter: 6 ft 0 in (1.83 m)
Empty weight: 473 lb (215 kg)
Max take off weight: 770 lb (349 kg)
Never-exceed speed: 135 mph (217 kmh)
Max level speed: 118 mph (190 kmh) at 2,000 ft (610 m)
Max cruise speed: 109 mph (175 kmh) at 2,000 ft (610 m)
Econ cruise speed: 100 mph (161 kmh) at 2,000 ft (610 m)
Stall speed: 42 mph (68 kmh)
Climb: 1,200 ft (366 m)/min
Service ceiling: 16,000 ft (4,875 m)
Take off run: 150 ft (46 m)
Take off to 50 ft (15 m): 300 ft (91 m)
Landing run from 50 ft (15 m): 400 ft (122 m)
Landing run: 300 ft (91 m)
Range: 466 mls (750 km)