Stoddard-Hamilton Glasair II
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.[1][2][3]
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.[1][2][3]
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 23.3 ft (7.1 m) span wing employs a NASA GA(W)-2 airfoil. The wings have an area of 81.3 sq ft (7.55 m2) and mount flaps. The acceptable power range for the Super II RG or Super II FT versions is 160 to 210 hp (119 to 157 kW), with the 180 hp (134 kW) Lycoming O-360 four-stroke powerplant a commonly used engine.[1][2][3][4][5]
The manufacturer estimates construction time for the Super II RG or Super II FT versions as 3000 hours.[1]
The Glasair II was later developed into the Glasair III.[1]
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.[1][5]
Variants
- Glasair Super II FT
- Fixed tricycle landing gear version, in production in 2011.[1][3]
- Glasair Super II RG
- Retractable tricycle landing gear version, in production in 2011.[1][3]
- Glasair Super II TD
- Fixed taildragger landing gear version, in production in 1998, but production presently completed.[2][3]
Specifications (Glasair Super II RG)
Data from Kitplanes[1]
General characteristics
- Crew: one
- Capacity: one passenger
- Length: 20.8 ft (6.3 m)
- Wingspan: 23.3 ft (7.1 m)
- Wing area: 81.3 sq ft (7.55 m2)
- Airfoil: NASA GA(W)-2
- Empty weight: 1,400 lb (635 kg)
- Gross weight: 2,100 lb (953 kg)
- Fuel capacity: 70 U.S. gallons (260 L; 58 imp gal)
- Powerplant: 1 × Lycoming O-360 four cylinder, air-cooled, four stroke aircraft engine, 180 hp (130 kW)
- Propellers: 2-bladed constant speed propeller
Performance
- Cruise speed: 221 mph (192 kn; 356 km/h)
- Stall speed: 73 mph (63 kn; 117 km/h)
- Range: 1,749 mi; 2,815 km (1,520 nmi)
- Rate of climb: 2,700 ft/min (14 m/s)
- Wing loading: 33.2 lb/sq ft (162 kg/m2)
References
- ↑ 1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 1.9 Vandermeullen, Richard: 2012 Kit Aircraft Buyer's Guide, Kitplanes, Volume 28, Number 12, December 2011, page 55. Belvoir Publications. ISSN 0891-1851
- ↑ 2.0 2.1 2.2 2.3 Downey, Julia: 1999 Kit Aircraft Directory, Kitplanes, Volume 15, Number 12, December 1998, page 68. Primedia Publications. ISSN 0891-1851
- ↑ 3.0 3.1 3.2 3.3 3.4 3.5 Purdy, Don: AeroCrafter - Homebuilt Aircraft Sourcebook, page 261. BAI Communications. ISBN 0-9636409-4-1
- ↑ Lednicer, David (2010). "The Incomplete Guide to Airfoil Usage". Retrieved 3 January 2012.
- ↑ 5.0 5.1 Bertrand, Noel; Rene Coulon; et al: World Directory of Leisure Aviation 2003-04, page 183. Pagefast Ltd, Lancaster UK, 2003. ISSN 1368-485X
External links
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