Sochen Phoenix
title: "Sochen Phoenix" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["ultralight-aircraft"] topic_path: "general/ultralight-aircraft" source: "https://en.wikipedia.org/wiki/Sochen_Phoenix" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0
::data[format=table title="Infobox aircraft"]
| Field | Value |
|---|---|
| aircraft_type | One/two seat microlight |
| national_origin | South Africa |
| designer | Edwin Sochen |
| number_built | 14 (both variants) by c.1985 |
| :: |
| name = | logo = | logo_size = | image = | alt = | caption = | long_caption = | other_names = | aircraft_type = One/two seat microlight | aim = | outcome = | related = | national_origin = South Africa | manufacturer = | design_group = | designer = Edwin Sochen | builder = | issuer = | status = | owners = | primary_user = | more_users = | service = | major_applications = | proposals = | prototypes = | number_built = 14 (both variants) by c.1985 | construction_number = | civil_registration = | military_serial = | radio_code = | requirement = | aircraft_carried = | flights = | total_hours = | total_distance = | construction_date = | introduction = | retired = | first_flight = | initiated = | in_service = | last_flight = | expected = | developed_from = | variants = | developed_into = | preservation = | fate = | predecessors = | successors = | concluded =
The Sochen Phoenix was a single engine, three axis control microlight designed and produced in small numbers in South Africa in the early 1980s.
Design and development
The original single seat ES-1 Phoenix began as a rebuild by Edwin Sochen of a storm-destroyed Quicksilver MX but emerged a much refined aircraft, with two-surface wings, ailerons rather than spoilers and a fully steerable undercarriage. One of these was built and flown, then Sochen developed it into the CII two-seater.
Seating apart, the two variants were generally similar. The two surface wing, tapered in plan with a straight leading edge and a forward swept trailing edge, was braced from below on each side by a single strut, assisted by jury struts. The ailerons filled the whole span. The fuselage of the Phoenix was a completely open aluminium frame structure which carried the exposed pilot's seat, placing his head just below the leading edge of the wing and supporting the engine in pusher configuration immediately behind. The fuselage frame extended rearwards to carry a conventional tail with horizontal surfaces at the same height as the wing and an all-moving rudder with a swept leading edge, extending below the tailplane aft of the rudder post. The rudder of the CII was swept on both edges, unlike that of the single seat version, and extended downwards further. The tricycle undercarriage had three similarly sized wheels mounted on short legs interconnected by a triangular frame. The front wheel was steerable from the rudder bar and the rear pair were differentially brakeable.
Operational history
The ES-1 was a one-off but, after two prototypes the CCII was put into production by Court Helicopters. Only eleven were completed before production was stopped.
Variants
;Phoenix ES-1: Original single seat version. ;Phoenix CCII: Two seat version, put into production with eleven built.
Specifications (CII)
|ref=Burger and Burr |prime units?=imp General characteristics
|genhide=
|crew=Two |capacity= |length m= |length ft= |length in= |length note= |span m=9.75 |height m= |height ft= |height in= |height note= |wing area sqm= |wing area sqft= |wing area note= |aspect ratio= |airfoil= |empty weight kg=143 |empty weight note= |gross weight kg= |gross weight lb= |gross weight note= |max takeoff weight kg= |max takeoff weight lb= |max takeoff weight note= |fuel capacity= |more general= Powerplant
|eng1 number=1 |eng1 name=Rotax 503 |eng1 type=air-cooled two-stroke with two inline cylinders |eng1 hp=52 |power original=
|more power=
|prop blade number=2 |prop name= |prop dia m=1.47 |prop dia note= Performance
|perfhide= |max speed mph=65 |max speed note= |cruise speed mph=50 |cruise speed note= |stall speed mph=28 |stall speed note= |never exceed speed kmh= |never exceed speed mph= |never exceed speed kts= |never exceed speed note= |minimum control speed kmh= |minimum control speed mph= |minimum control speed kts= |minimum control speed note= |range miles=100 |range note= at average cruising speed |endurance= |ceiling m= |ceiling ft= |ceiling note= |g limits= |roll rate= |glide ratio= |climb rate ftmin=350 |climb rate note= from sea level |time to altitude= |wing loading kg/m2= |wing loading lb/sqft= |wing loading note= |power/mass=
|more performance=
- Take-off distance: 230 ft (70 m)
- Landing distance: 100 ft (30 m)
|see also= |related= |similar aircraft= |lists=
References
References
- Berger, Alain-Yves. (1985). "Ultralight and Microlight Aircraft". Haynes Publishing Group.
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