The Stoddard-Hamilton Glasair II is an American amateur-built aircraft that was designed by Tom Hamilton and produced by Stoddard-Hamilton Aircraft and later Glasair Aviation as a kit for amateur construction. It was first flown in 1989, and remained in production in 2012.

Design and development

A development of the earlier Glasair I, the Glasair II features a cantilever low-wing, a two-seats-in-side-by-side configuration enclosed cockpit accessed via gull-winged doors, fixed or retractable tricycle landing gear or fixed conventional landing gear and a single engine in tractor configuration.

The Glasair II was designed to FAR Part 23 standards and was extensively tested. Its wing has been tested to +10.5g. As indicated by its name, the aircraft is made from fiberglass. Its 23.3ft (7.1m) span wing employs a NASA GA(W)-2 airfoil. The wings have an area of 81.3sqft (7.55m2) and mount flaps. The acceptable power range for the Super II RG or Super II FT versions is 160 to 210hp (119 to 157kW), with the 180hp (134kW) Lycoming O-360 four-stroke powerplant a commonly used engine.

The manufacturer estimates construction time for the Super II RG or Super II FT versions as 3000 hours.

The Glasair II was later developed into the Glasair III.

Operational history

By December 2011 there were 1200 examples reported completed and flying making it one of the most successful two seat kit aircraft ever designed.

Variants

Glasair II-S

Glasair II-S

12in (30cm) stretch

Glasair II FT

Glasair Super II FT

Fixed tricycle landing gear version, in production in 2011.

Glasair RG

Glasair Super II RG

Retractable tricycle landing gear version, in production in 2011.

Glasair Super II TD

Fixed taildragger landing gear version, in production in 1998, but production presently completed.

Specifications (Glasair Super II RG)

Data from Kitplanes

General characteristics

  • Crew: one
  • Capacity: one passenger
  • Length: 20.8ft (6.3m)
  • Wingspan: 23.3ft (7.1m)
  • Wing area: 81.3sqft (7.55m2)
  • Airfoil: NASA GA(W)-2
  • Empty weight: 1,400lb (635kg)
  • Gross weight: 2,100lb (953kg)
  • Fuel capacity: 70 U.S. gallons (260L; 58impgal)
  • Powerplant: 1 × Lycoming O-360 four cylinder, air-cooled, four stroke aircraft engine, 180hp (130kW)
  • Propellers: 2-bladed constant speed propeller

Performance

  • Maximum speed: 238mph (383km/h, 207kn)
  • Cruise speed: 221mph (356km/h, 192kn)
  • Stall speed: 73mph (117km/h, 63kn)
  • Range: 1,750mi (2,820km, 1,520nmi)
  • Rate of climb: 2,700ft/min (14m/s)
  • Wing loading: 25.8lb/sqft (126kg/m2)

External links