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SOLO Aircraft Engine 2625 02 i


General engine description
- Twin - cylinder in line - two - stroke - engine
- Liquid cooling
- Lubrication by fuel-oil-mixture
- Electronic fuel injection
- Dual electronic high-voltage ignition
- Redundancy system
- Crankshaft layout for belt transmission
- AC generator

Download of technical drawing as pdf-file here.

Technical data
Engine Displacement 625 ccm, cyl. bore 76 mm, stroke 69 mm
Compression rartio 9.5 : 1
Ignition unit Electronic, two butterfly shutters, mapped
Ignition plugs BOSCH W5 AC Gap at electrodes 0.5 mm
Fuel injection Electronic, two butterfly shutters, mapped
Direction of rotation Clockwise, seen in direction of flight
Fuel 2-Stroke mix, AVGAS 100LL, premium gas (min. 95 ROZ)
Mixture Mixture ratio 1 : 50 , 2-stroke Castrol mineral oil or synthetic oil, or other oils with specification according to JASO FC oder FD
Dry Weight approx. 24 kg without exhaust (according to airframe manufacturer)
Generator 12 V 500 W
Coolant Engine coolant (Glysantin BASF G48), tab water (0-20°dh) in a
mixture of 40:60 (27°C)


Operational data and limitations
Take-off-speed, power 6,600 1/min. at a power of 50 kW (68 HP)
Max. cont. speed, power 6,600 1/min. at a power of 50 kW (68 HP)
Max. rpm 6,700 1/min
Cut off speed by CPU 6,700 1/min.
Idle rpm approx. 2,300 1/min
Max. temp. cooling liquid 115 °C (240°F) measured in the cylinder - head
Fuel consumption Max. continous power approx. 6.47 US gal./hr. (24.5 l/hr.)