The Las Brisas Mohawk is an American homebuilt aircraft that was designed and produced by Las Brisas Sales of Ozark, Missouri. When it was available the aircraft was supplied in the form of plans for amateur construction.

Based upon the Avid Flyer, which it greatly resembles, the Mohawk features a strut-braced high wing, a two-seats-in-side-by-side configuration enclosed cockpit accessed via doors, fixed conventional landing gear and a single engine in tractor configuration.

The aircraft is made from metal tubing, with its flying surfaces and fuselage covered doped aircraft fabric. Its 30.00 ft (9.1 m) span wing features Junkers flaperons, has a wing area of 124.5 sq ft (11.57 m2) and is supported by “V” struts with jury struts. The plans specify standard hydraulic brakes, a steerable tailwheel and wings that fold for ground transport or storage. The standard engine used is the 50 hp (37 kW) Rotax 503 two-stroke powerplant, which gives a standard day, sea level takeoff distance of 100 ft (30 m) and a landing roll of 150 ft (46 m).

The Mohawk has a typical empty weight of 450 lb (200 kg) and a gross weight of 1,000 lb (450 kg), giving a useful load of 550 lb (250 kg). With full fuel of 12 U.S. gallons (45 L; 10.0 imp gal) the payload for pilot, passenger and baggage is 478 lb (217 kg).

The manufacturer estimated the construction time from the supplied plans as 900 hours. In 1998 the designer indicated that the aircraft could be completed for US$6,500 excluding labor. In 1998, plans were sold for US$229.00 but by 2014 were no longer available.

Mohawk
Engine: 1 × Rotax 503, 50 hp (37 kW)
Propeller: 2-bladed wooden
Wingspan: 30 ft 0 in (9.14 m)
Wing area: 124.5 sq ft (11.57 m2)
Length: 18 ft 0 in (5.49 m)
Empty weight: 450 lb (204 kg)
Gross weight: 1,000 lb (454 kg)
Fuel capacity: 12 U.S. gallons (45 L; 10.0 imp gal)
Maximum speed: 130 mph (209 km/h; 113 kn)
Cruise speed: 85 mph (137 km/h; 74 kn)
Stall speed: 30 mph (48 km/h; 26 kn) flaperons down
Range: 320 mi (278 nmi; 515 km)
Service ceiling: 12,000 ft (3,700 m)
Rate of climb: 1,200 ft/min (6.1 m/s)
Wing loading: 8.0 lb/sq ft (39 kg/m2)
Crew: one
Capacity: one passenger

A Part 103 legal ultralight first flown in 1995, the wings are sheet dural.

Top speed: 65 mph
Cruise: 55 mph
Stall: 26 mph
Rate of climb: 1000 fpm
Takeoff dist: 150 ft
Landing dist: 100 ft
Service ceiling: 10,000 ft
Engine: Rotac 447, 30 hp
HP range: 30-40
Fuel capacity: 5 USG
Empty weight: 250 lb
Gross weight: 550 lb
Height: 4.5 ft
Length: 21 ft
Wing span: 26 ft
Wing area: 117 sq.ft
Seats: 1
Landing gear: tailwheel

Engine: Rotax 447, 40 hp
Wing span: 7.92 m
Wing area: 10.90 sq.m
MAUW: 249 kg
Empty weight: 113 kg
Fuel capacity: 19 lt
Max speed: 128 kph
Cruise speed: 80 kph
Minimum speed: 40 kph
Climb rate: 5 m/s
Fuel consumption: 7.5 lt/hr
Seats: 1
Kit price (1998): $4900

First flown in 1992.

Top speed: 100 mph
Cruise: 85 mph
Stall: 53 mph
Range: 140 sm
Rate of climb: 800 fpm
Takeoff dist: 200 ft
Landing dist: 200 ft
Service ceiling: 15,000 ft
Engine: Rotax 582, 65 hp
HP range: 48-80
Fuel capacity: 11 USG
Empty weight: 400 lb
Gross weight: 900 lb
Height: 6.5 ft
Length: 21 ft
Wing span: 32 ft
Wing area: 170 sq.ft
Seats: 2 tandem
Landing gear: nosewheel

The Skylark lightweight ultralight was deve¬loped by Ron Lang of Skylark engine fame. The double surface wings have leading and trailing edge spars made of aluminium tube which have compression struts diagonally braced with cables and formed tube ribs are riveted to the spars.

Engine: Skylark 28 hp.
Prop: 121 cm x 66 cm pitch.
Wing span: 8.5 m.
Econ cruise speed: 35-40 kts.
Stall: 22 kts.
Construction time: 30 hrs.