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Quad City Challenger


Single-seat single-engined high-wing mono-plane with conventional three-axis control. Wing has unswept leading and trailing edges, and constant chord; cruciform tail. Pitch control by elevator on tall; yaw control by fin-mounted rudder; roll control by spoilers; control inputs through stick for pitch/roll and pedals for yaw. Wing braced from below by struts; wing profile; double-surface. Undercarriage has three wheels in tricycle formation, with additional tailwheel. Suspension on all wheels. Push-right go-right nosewheel steering connected to yaw control. Aluminium-tube framework, partially enclosed. Engine mounted at wing height driving pusher propeller.

Designed by Dave Goulet and first flown in 1983, this ultralight made its debut at Sun 'n' Fun in March 1983 at Lakeland, Florida. Thanks to the fabric covering the whole of the framework and a windscreen over the cockpit area, it has an excellent glide ratio, 11/1 being claimed by the manufacturer. At that time little detailed information was available from Quad City Ultralights on what was really no more than a prototype, but since then the Challenger has gone on sale as a kit requiring 50 h for completion and costing $5495. Rigging time is expected to be in the order of 30 min by one person from a trailer, according to the manufacturer. The aircraft can also be towed on its own undercarriage.

Power comes from the KFM 107 with electric start and reduction drive.




In 2010 LSA Quick-build kits were from US$9,215 to US$12,965 ex engine  and engine options were Hirth F-33, Rotax 447/503/582, and HKS 700E.

The Challenger qualifies for Part 103 ultralight or 51% kit for Experimental - Amateur-Built, can be flown with Sport Pilot Permit, and qualifies as a Light Sport Aircraft.

Engine: KFM 107ERV, 25 hp at 6000 rpm
Propeller diameter and pitch 52 x 24 inch, 1.32 x 0.61 m
V-belt reduction, ratio 2.0/1
Power per unit area 0.20 hp/sq.ft, 2.1 hp/sq.m
Fuel capacity 5.0 US gal, 4.2 Imp gal, 18.9 litre
Length overall 18.8 ft, 5.72 m
Height overall 6.0ft, 1.83m
Wing span 32.0ft, 9.75m
Constant chord 4.0 ft, 1.22 m
Sweepback 0 degs
Total wing area 128 sq.ft, 11.9sq.m
Wing aspect ratio 8.0/1
Empty weight 242 lb, 110kg
Max take-off weight 530 lb, 240kg
Payload 288 lb, 131kg
Max wing loading 4.14 lb/sq.ft, 20.2 kg/sq.m
Max power loading 21.2 lb/hp, 9.6kg/hp
Max level speed 63 mph, 101 kph
Never exceed speed 70 mph, 113 kph
Max cruising speed 60 mph, 97 kph
Stalling speed 28 mph, 45 kph
Max climb rate at sea level 700 fpm, 3.6 m/s
Best glide ratio with power off 11/1
Service ceiling 10,000 ft, 3050 m

Engine: Rotax 277 (268 cc). 28 hp
Static thrust: 235 lbs
HP range: 28-40
Empty weight: 242 lb
Max weight: 500 lb
Wing span: 31ft 6in
Wing area: 142 sq.ft
Height: 6 ft
Length: 18 ft 6 in
Wing loading: 3.52 lbs/sq.ft
Power loading: 17.86 lbs/hp
Fuel cap: 5 USG
Construction: Aluminium, Dacron
Max speed: 63 mph
Cruise: 55 mph
Stall: 25 mph
Vne: 80 mph
Cross-wind capability: 25 mph
Climb rate: 500-700 fpm @ 40 mph
Design load: +4, -2.5g
Glide: 10-1
Seats: 1
Range: 150 sm
Take off dist: 150 ft
Ldg dist: 150 ft
Service ceiling: 12,500 ft

Quad City Ultralights Aircraft Challenger UL
Engine: Rotax 447, 40 hp
HP range: 28-50
Length: 18.5 ft
Wing span: 31.5 ft
Wing area: 142 sq.ft
Empty weight: 254 lb
Gross weight: 500 lb
Fuel capacity: 5 USG
Cruise: 55 mph
Stall: 27 mph
Range: 140 sm
Rate of climb: 700 fpm
Takeoff dist: 250 ft
Landing dist: 250 ft
Cockpit width: 24 in
Landing gear: nosewheel


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