Verner JCV 360
From Wikipedia, the free encyclopedia
The Verner JCV 360 is a Czech aircraft engine, designed and built by Verner Motor of Šumperk for use in ultralight aircraft.[1]
| JCV 360 | |
|---|---|
| Type | Aircraft engine |
| National origin | Czech Republic |
| Manufacturer | Verner Motor |
| Major applications | |
| Manufactured | up until about 2013 |
Design and development
The engine is a twin cylinder, 360 cc (22.0 cu in), horizontally-opposed four-stroke, liquid-cooled, gasoline engine design, with a poly V belt reduction drive with reduction ratio of 2.76:1. It employs a single electronic ignition and produces 35 hp (26 kW) at 7800 rpm.[1]
The engine was still advertised for sale on the company website in 2013, but by 2015 was no longer listed as available and it is likely that production has ended.[2]
Applications
Specifications (JCV 360)
Data from World Directory of Leisure Aviation 2011-12[1]
General characteristics
- Type: Twin cylinder, horizontally-opposed, four stroke aircraft engine
- Bore: 63 mm (2.5 in)
- Stroke: 58 mm (2.3 in)
- Displacement: 360 cc (22.0 cu in)
- Length: 580 mm (22.8 in)
- Width: 340 mm (13.4 in)
- Height: 360 mm (14.2 in)
- Dry weight: 30.5 kg (67.2 lb)
Components
- Fuel type: gasoline
- Cooling system: liquid
- Reduction gear: poly V belt reduction drive, reduction ratio of 2.76:1
Performance
- Power output: 35 hp (26 kW) at 7800 rpm
- Compression ratio: 11:1