Photograph:
Rand KR-1 ZK-EKT (c/n AACA/451) at Taupo, New Zealand in 1997 (Keith Morris – NZCIVAIR)
Country of origin:
United States of America
Description:
Single-seat light sport monoplane
Power Plant:
One 67 kw (90 hp) modified Volkswagen four-cylinder horizontally-opposed air-cooled engine
Specifications:
- Wingspan: 5.18 m (17 ft)
- Length: 3.89 m (12 ft 9 in)
- Height: 1.07 m (3 ft 6 in)
- Wing area: 5.76 m² (62 sq ft)
- Max speed at sea level: 354 km/h(220 mph)
- Max cruising speed at 1,525 m (5,000 ft): 354 km/h (220 mph)
- Economical cruising speed at 5,485 m (18,000 ft): 402 km/h (250 mph)
- Stalling speed: 73 km/h (45 mph)
- Max rate of climb at sea level: 457 m/min (1,500 ft/min)
- Service ceiling: 9,145 m (30,000 ft)
- Range with max fuel: 4,825 km (3,000 miles)
- Empty weight: 218 kg (480 lb)
- Loaded weight: 408 kg (900 lb)
History:
Rand Robinson Engineering Inc of Huntington Beach, California, was formed in the United States in 1974 to market plans for the KR-1 single-seat and KR-2 two-seat series of amateur constructed aircraft. The first of the series, the KR-1, was flown for the first time in February 1972 fitted with a 27 kw (36 hp) [1200 cc] converted Volkswagen motor vehicle engine. It was subsequently re-engined with a 43 kw (58 hp) [1700 cc] conversion of the Volkswagen. More than 6,000 sets of plans and kits of the series have been sold around the world. The KR-1 can be fitted with engines up to the VW 2100 cc. The KR-2S, a stretched variant which is 40.6 cm (16 inches) longer and has 7.6 cm (3 in) more head room in the cockpit, can take engines up to 75 kw (100 hp). The KR-1B varies from the KR-1 in having modified outer wing sections.
First and only example of the type completed in New Zealand was a KR-1, ZK-EKT (c/n AACA/451) which, based at Taupo for a period, was fitted with a 46 kw (62 hp) Walter Mikron four-cylinder in-line air-cooled engine previously fitted to the Belgian-built Tipsy Belfair ZK-BGZ. A project to build a KR-1 was commenced by Mr G Gill of Wagga Wagga, NSW and the regisration VH-TXX ws allotted but the aircrzct is not known to have been completed.
The wing of the aircraft is of composite structure with a spruce front spar, and spruce and plywood rear spar. Most ribs are formed from styrofoam plastics, the spaces between being filled with styrofoam slab. The whole wing structure is then filled with Dynel epoxy. The lower half of the fuselage is of spruce and plywood, and the upper part of carved styrofoam, also covered with Dynel epoxy. The tail unit is of spruce and carved styrofoam, with similar covering to the wing. A retractable tailwheel type undercarriage is usually fitted but it may be fitted with a tricycle undercarriage.