1. Design and development

2. Operational history

3. Specifications (Condor S Sport)

4. References

5. External links

The Southern Condor is an American powered parachute that was designed and produced by Southern Powered Parachutes (formerly called Condor Powered Parachutes) of Nicholson, Georgia. Now out of production, when it was available the aircraft was supplied as a complete ready-to-fly-aircraft.^[1][2][3]

The company seems to have gone out of business about 2006 and production ended.^[4]

Design and development

The Condor complies with the Fédération Aéronautique Internationale microlight category, but was never an accepted US light-sport aircraft.^[1][5]

The Condor features a {{convert|540|sqft|m2|abbr=on}} parachute-style wing, two-seats-in-tandem accommodation, tricycle landing gear and a single {{convert|64|hp|kW|0|abbr=on}} Rotax 582 engine in pusher configuration. Twin {{convert|50|hp|kW|0|abbr=on}} Rotax 503 engines were a factory option.^[1]

The aircraft carriage was built from a combination of bolted aluminium and 4130 steel tubing by Aerostar of Romania and then assembled in the US. In flight steering is accomplished via foot pedals that actuate the canopy brakes, creating roll and yaw. On the ground the aircraft has lever-controlled nosewheel steering. The main landing gear incorporates spring rod suspension.^[1][6]

Operational history

In June 2015, 13 examples were registered in the United States with the Federal Aviation Administration, although a total of 15 had been registered at one time.^[7]

Specifications (Condor S Sport)

|genhide=
|crew=one
|capacity=one passenger
|length m=
|length ft=9.8
|length in=
|length note=
|width m=
|width ft=6
|width in=4.5
|width note=
|span m=
|span ft=
|span in=
|span note=
|height m=
|height ft=7
|height in=
|height note=
|wing area sqm=50
|wing area sqft=
|wing area note=
|aspect ratio=
|airfoil=
|empty weight kg=146
|empty weight lb=
|empty weight note=
|gross weight kg=
|gross weight lb=
|gross weight note=
|fuel capacity={{convert|10|u.s.gal}}
|more general=

|eng1 number=1
|eng1 name=Rotax 582
|eng1 type=twin cylinder, two-stroke, liquid-cooled aircraft engine
|eng1 kw=
|eng1 hp=64
|prop blade number=4
|prop name=Ivoprop, composite, ground adjustable
|prop dia m=
|prop dia ft=
|prop dia in=
|prop note=

|perfhide=Y
|max speed kmh=
|max speed mph=
|max speed kts=
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|cruise speed kts=
|cruise speed note=
|stall speed kmh=
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|stall speed kts=
|stall speed note=
|never exceed speed kmh=
|never exceed speed mph=
|never exceed speed kts=
|never exceed speed note=
|range km=
|range miles=
|range nmi=
|range note=
|endurance=
|ceiling m=
|ceiling ft=
|ceiling note=
|g limits=
|roll rate=
|glide ratio=
|climb rate ms=
|climb rate ftmin=
|climb rate note=
|time to altitude=
|sink rate ms=
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|sink rate note=
|lift to drag=
|wing loading kg/m2=
|wing loading lb/sqft=
|wing loading note=
|power/mass=
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|more performance=
|avionics=
}}

References

External links

• [https://web.archive.org/web//http://www.condorppc.com/ Company website archives] on Archive.org

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• Stevenson-Wydler Technology Innovation Act
• Stevenson-Wydler Technology Innovation Act of 1980
• Stevenson-Wydler Technology Innovation Act of 1980 (P.L. 96-480)
• Steven Sotloff