Vertical Hummingbird
# Vertical Hummingbird

The Vertical Hummingbird is an American helicopter, produced by Vertical Aviation Technologies of Sanford, Florida that was introduced in 1991. The aircraft is supplied as a kit for amateur construction.

## Design and development

The Hummingbird is a development of the certified Sikorsky S-52 that first flew in 1947, adapted to kit form. The aircraft features a single main rotor, a four-seat enclosed cabin, quadracycle landing gear and an option for skids. The prototype was converted by Vertical Aviation Technologies from a Sikorsky S-52-3.

The Hummingbird fuselage is made from riveted aluminum sheet. The nose section is adapted from the Bell 206. Its 33 ft (10.1 m) diameter fully articulated three-bladed main rotor employs a NACA 0015 airfoil. The two-bladed tail rotor has a diameter of 5.75 ft (1.8 m). The aircraft has an empty weight of 1,790 lb (812 kg) and a gross weight of 2,800 lb (1,270 kg), giving a useful load of 1,010 lb (458 kg). With full fuel of 57 U.S. gallons (220 L; 47 imp gal) the payload is 668 lb (303 kg).

## Variants

### VAT S-52-3

    Prototype of the Hummingbird family, converted from an original Sikorsky S-52-3.

### Hummingbird 260L

    Version powered by a six cylinder, air-cooled, four-stroke, dual-ignition 265 hp (198 kW) Lycoming IVO-435 engine

### Hummingbird 300LS

    Version powered by an eight cylinder, liquid-cooled, four-stroke, single-ignition 325 hp (242 kW) General Motors LS7 V-8 automotive conversion engine, derated to 280 hp (209 kW)

### Hummingbird 300L

    Version powered by a six cylinder, air-cooled, fuel injected IO-540 derated to 280 hp (209 kW)

## Specifications (Hummingbird 300L)

Data from Vertical Aviation

General characteristics

* Crew: one
* Capacity: three passengers
* Width: 5 ft 0 in (1.52 m)
* Height: 8 ft 7 in (2.62 m)
* Airfoil: NACA 0015
* Empty weight: 1,790 lb (812 kg)
* Gross weight: 2,800 lb (1,270 kg)
* Fuel capacity: 57 US gallons (47 imp gal; 220 L)
* Powerplant: 1 × IO-540 six cylinder, air-cooled, four stroke fuel injected aircraft engine, 280 hp (210 kW)
* Main rotor diameter: 33 ft 0 in (10.06 m)

Performance

* Maximum speed: 110 mph (180 km/h, 96 kn)
* Never exceed speed: 110 mph (180 km/h, 96 kn)
* Range: 380 mi (610 km, 330 nmi)
* Service ceiling: 14,000 ft (4,300 m)
* Rate of climb: 950 ft/min (4.8 m/s) at 2,800 lb (1,270 kg)
