The Lascurair XB-1 was a four-seat cabin monoplane built in 1939 as a small charter aircraft but only one prototype was completed.
Of all-wood construction with fabric and plywood covering, power was provided by two 65 hp Continental C65.
This was employed by a small airline in South-East Mexico for several years before becoming privately owned.
Engines: 2 x Continental C65, 65 hp
Max speed: 130 mph
Cruise: 112 mph
Service ceiling: 19,685 ft
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
The Model C Speedbird (N38C or NX38C) by Merle Larson of Oakland, Ca. had a small wing (wingspan 12ft) designed to work within the slipstream of the propeller and featured very large flaps for lift.
The Speedbird aircraft was modified from a Taylorcraft BC-12.
The aircraft flew, but on that first flight on 7 December 1953 the engine stopped and the aircraft stalled. Larson escaped serious injury and later designed the (Larson-Holmes) D-1 Duster.
The Larson F-12 Baby was a sports biplane built in the US in the early 1960s. It was intended to produce it ready to fly or homebuilt from kits or plans but only one was completed.
The Baby was a single bay single engine, single seat biplane with stagger. The wings were wooden structures with two spars and fabric covering; the upper wing had 1° of dihedral and the lower one 3°. There were ailerons on both wings, with aluminium frames and again fabric covered. The fuselage and empennage were fabric covered, welded steel structures. It had fixed conventional landing gear with rubber sprung main legs, aluminium wheels with brakes and a sprung tailwheel.
The Baby was powered by an 85 hp (63 kW) Continental C85, its fuel tank in the fuselage behind the engine and in front of the single seat, open cockpit, anf firdt flew in 1961.
Powerplant: 1 × Continental C85, 85 hp (63 kW)
Propeller: 2-bladed McCauley aluminium, fixed pitch
Wingspan: 17 ft 0 in (5.18 m) upper and lower
Wing area: 73 sq ft (6.8 m2)
Aspect ratio: about 7 on upper wing, 6 on lower
Airfoil: NACA 4412 modified
Length: 17 ft 0 in (5.18 m)
Height: 5 ft 6 in (1.68 m)
Empty weight: 500 lb (227 kg) weights estimated
Gross weight: 800 lb (363 kg)
Fuel capacity: 12 US gal (10.0 imp gal; 45 l)
Maximum speed est: 130 mph (210 km/h, 110 kn)
Cruise speed est: 110 mph (180 km/h, 96 kn)
Rate of climb est: 2,000 ft/min (10 m/s)
Crew: One
An ultralight single-seat biplane in 1960.
In 1955, Merle Larson designed the D-1 with updated features to improve cropdusting compared to the popular Boeing Stearman in use at the time. The aircraft used only 25 percent of the number of parts as a Stearman.
The biplane featured a steel tube fuselage, and aluminum covered wings. The fuselage was fabric covered only to behind the cockpit, leaving the rest of the tail structure exposed, preventing dust buildup in the tail. The aircraft had twin rudders mounted outboard of the spray trail. Each of these were all-moving with anti-servo tabs. Standard automotive wheels and tires were employed to reduce cost as low-cost World War II surplus was becoming too old, and new aviation tires cost nearly five times as much.
Powerplant: 1 × Lycoming R-680, 225 hp (168 kW)
or 220 hp (164 kW) Continental R-670
or 245 hp (183 kW) Jacobs R-755
Propeller: 2-blade McCauley ground-adjustable propeller
Upper wingspan: 30 ft 0 in (9.14 m)
Lower wingspan: 33 ft 0 in (10.06 m)
Wing area: 315 sq ft (29.3 m2)
Aspect ratio: 6
Airfoil: Göttingen 365
Length: 25 ft (7.6 m)
Height: 11 ft 00 in (3.35 m)
Empty weight: 1,700 lb (771 kg)
Gross weight: 3,600 lb (1,633 kg)
Fuel capacity: 30 US gal (25 imp gal; 114 l) fuel ; 4.4 US gal (3.7 imp gal; 16.7 l)
Cruise speed: 90 mph (140 km/h, 78 kn) at sea level
Landing speed: 40 mph (35 kn; 64 km/h)
Stall speed: 40 mph (64 km/h, 35 kn)
Rate of climb: 1,400 ft/min (7.1 m/s) at sea level, empty
Wing loading: 11.4 lb/sq ft (56 kg/m2)
Take-off run, empty, nil wind: <200 ft (61 m)
Take-off run, 1,000 lb (454 kg) payload, nil wind: 600 ft (183 m)
Crew: 1
USA
Based at Concord, California, produced the D.1. agricultural aircraft in 1959 and the F-2 Baby ultralight single-seat biplane in 1960.
The 1931 Larsen 2-C, built by Herman Larsen, was a Ford-powered home-built registered N769N c/n 2.
Herman Larsen
Keasbey NJ.
USA
Built the Larsen 2-C in 1931.
Designed by Carl Larsen in Norway in the 1950s, the LN-11 is a single seat, all-metal sport plane with retractable undercarriage.
Engine: Continental C90, 90 hp
Span: 22 ft
Length: 20 ft
AUW: 900 lb
Max speed: 165 mph
