Star Aircraft Company, Bartlesville, Oklahoma
Specifications from Aero Digest, April, 1935:
• President: John H. Kane. Vice-president, General Manager and Sales Manager: Billy Parker. Chief Engineer: Charles Peters.
Two-place high-wing monoplane. A TC 321. Lambert R-266 engine, 90 horsepower.
Span 31 feet. Length overall 20 feet 1 inch. Height overall 6 feet 8 inches. Wing area 142 square feet. Power loading 15.8 pounds per horsepower. Wing loading 10 pounds per square foot.
Empty weight 919 pounds. Useful load 506 pounds. Payload 185 pounds. Gross weight 1425 pounds. Fuel capacity 22 gallons. Oil capacity 2.5 gallons.
Maximum speed at 2300 r.p.m. 105 miles per hour. Cruising speed at 2000 r.p.m. 90 miles per hour. Landing speed 38 miles per hour. Service ceiling 16,000 feet. Rate of climb 750 feet per min. Cruising range 360 miles.
Fuselage: welded steel tube structure, fabric covered; side-by-side seating arrangement; single control column with extension for dual control provided; luggage compartment is behind the seats; windows in front and sides of cockpit, with the front windshield extending from the leading edge of the wing to the top of the fuselage. Wing: two solid I -section spruce spars; Warren truss spruce ribs; fabric covered; wings in two sections attached to two cross tubes welded across and above the fuselage longerons; braced by parallel steel tube struts to the bottom fuselage longerons; narrow chord ailerons. Tail group: welded steel tube framework, fabric covered; adjustable stabilizer. Fixed divided-type landing gear; top of shock struts anchored to top fuselage longerons with bottom ends hinged to bottom fuselage longerons by steel tube Vees ; equipped with 26 X 5 tires, Bendix wheels and brakes, Warner shock absorbers.
Standard equipment includes Fahlin wood propeller.
Instruments: oil temperature gauge, oil pressure gauge, altimeter, tachometer.