Sonex Aircraft SubSonex

Design and development

The JSX-1 is a single place, single engine, jet aircraft similar in design to an Onex, with a Waiex style Y tail. It was introduced at AirVenture 2009. It is powered by a Czech-built PBS TJ-100 turbojet engine mounted above the aft fuselage, with the exhaust exiting between the Y-tail. The SubSonex achieved first engine test runs in December 2009. The engine produces 1100 N (240 lb) of thrust. Originally developed with only a central mono pod wheel, tail wheel and small wing tip outriggers, the prototype developed directional controllability problems during taxi-tests.

The production model of the SubSonex is the JSX-2. The landing gear was changed to a tricycle configuration with a manually retractable nosewheel. It was flight tested by Jet-sailplane performer Bob Carlton in August 2011.

At AirVenture 2013 the company began taking US$10,000 deposits on production kits. The projected price of the kit was US$125,000 in 2013 and US$135,000 in 2014.

The first JSX-2 kit was shipped to a customer in February 2015 and was completed and flown in October 2015.

Operational history

By May 2016 six examples had been registered in the United States with the Federal Aviation Administration.

Variants

JSX-1

Prototype version.

JSX-2

Second version with a BRS parachute, wider fuselage, more streamlined nose, and fully retractable undercarriage. Bob Carlton performed the first test flight with the prototype JSX-2 on 10 July 2014 from Wittman Field. Entered production as an amateur-built kit in the fall of 2014.

Specifications (JSX-2)

Data from Sonex Aircraft and AINonline

General characteristics

Crew: 1

Length: 16 ft 6 in (5.03 m)

Wingspan: 18 ft (5.5 m)

Wing area: 60 sq ft (5.6 m²)

Airfoil: 64-415

Empty weight: 500 lb (227 kg) average

Gross weight: 1,000 lb (454 kg) utility configuration

Fuel capacity: 40 U.S. gallons (150 L; 33 imp gal)

Powerplant: 1 × PBS TJ-100 turbojet

Performance

Cruise speed: 209 kn; 386 km/h (240 mph) TAS

Stall speed: 50 kn; 93 km/h (58 mph) landing configuration

Never exceed speed: 249 kn; 462 km/h (287 mph)

Range: 417 nmi; 772 km (480 mi) with 30 minute reserve

g limits: +4.4/-2.2 in utility configuration, +6/-3 in aerobatic configuration

Rate of climb: 1,600 ft/min (8.1 m/s) initial at sea level

Fuel consumption: 18 US gallons (68 L) per hour

Avionics

MGL Avionics Flight II instrument and the MGL V10 Com transceiver