Schweizer SA 1 30

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 utilizing some 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.

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.

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 A65 , 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)