Schweizer SA 1-30

Schweizer SA 1-30
Role	Homebuilt aircraft
National origin	United States of America
Manufacturer	Schweizer Aircraft
First flight	1 August 1958
Number built	One
Developed from	Schweizer SGS 1-26

The Schweizer SA 1-30 was the first entry by Schweizer in the powered aircraft market.^[1]

Design and development

Schweizer developed a line of gliders starting in World War II. The 1-30 was not intended to be a motor glider, but rather a light aircraft with some utilizing glider and sailplane technologies, common parts with other Schweizer designs, and an affordable price as a result of using smaller powerplants. Removable wings, and the ability to be transported by trailer were also criteria for keeping airport-based hangar costs down.^[2]

The 1-30 shares the same wings and tail surfaces as the 1-26 glider. The fuselage is of aluminum construction with a welded steel tube tail structure. The wings are removable using the same design as the 1-26. The engine uses a cowling with exposed cylinders like a J-3 Cub for simplicity and cooling efficiency. Wing mounted spoilers were retained from the 1-26, allowing steep low-speed descents at about a 5:1 glide ratio. Three sets of wings were tested including a set from a model 2-31.

Operational history

Construction of the prototype was started in April 1958 and completed by August. The aircraft was tested as a glider aero-towing aircraft using a Schweizer SGU 2-22C. The single-place 1-30 was not intended to go into production, the two-place version was envisioned as the production model, but was not produced.

Variants

SAU 1-30

The SA 1-30 modified with a 4 ft (122 cm) shorter wing and a fully cowled engine.^[3]

Two place variant

A two-place variant was intended. The 1-30 was tested with ballast to verify performance.

Specifications (Schweizer SA 1-30)

Data from Sport Aviation

General characteristics

• Capacity: 1
• Length: 20 ft 3 in (6.17 m)
• Wingspan: 40 ft (12 m)
• Wing area: 160 sq ft (15 m²)
• Aspect ratio: 10
• Empty weight: 700 lb (318 kg)
• Gross weight: 1,100 lb (499 kg)
• Powerplant: 1 × Continental A-65 , 65 hp (48 kW)

Performance

• Maximum speed: 96 kn; 177 km/h (110 mph)
• Cruise speed: 87 kn; 161 km/h (100 mph)
• Stall speed: 33 kn; 61 km/h (38 mph)
• Rate of climb: 1,000 ft/min (5.1 m/s)

References

1. Sport Aviation. March 1959. Missing or empty |title= (help)
2. Soaring. November–December 1958. Missing or empty |title= (help)
3. "The Aerosente Glider Workshop". Retrieved 21 June 2011.