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Aircraft specifications


General specifications

  • Certified for flight into known icing conditions
  • Pressurized cabin
  • Two (2) Pratt & Whitney PT6A-28 turbine engines
  • 620 shaft horsepower per engine
  • Two (2) three blade propellers, constant-speed, reversible and fully feathering
  • 34' 8" length; 12' 9" height; 42' 8" wingspan
  • 374 gallons fuel capacity (Jet A)


  • 9050 lbs maximum ramp weight
  • 9000 lbs takeoff weight
  • 9000 lbs landing weight
  • 7200 lbs zero fuel weight
  • 5020 lbs typical empty weight
  • 3980 lbs typical useful load

Performance - Both Engines (Maximum Takeoff Weight)

  • 283 kts max speed
  • 269 kts max recommended cruise
  • 75 kts stall speed in landing configuration
  • 31,600 feet all engine service ceiling
  • 2,710 feet per minute all-engine rate of climb
  • 1980 feet for take off over 50 foot obstacle
  • 1410 foot take off ground roll
  • 2480 feet landing over 50 foot obstruction
  • 1430 foot landing ground roll

Performance - Single Engine (Maximum Takeoff Weight)

  • 91 knots minimum control airspeed
  • 14,600 feet single-engine service ceiling
  • 660 feet per minute single-engine rate of climb
  • Cargo capacity – the SOAR research aircraft is capable of carrying a load of 1000 pounds in addition to a scientific crew of four persons and maximum fuel.
  • Maximum altitude – the maximum altitude of the SOAR research aircraft is its service ceiling at 31,600 feet for a minimum on-station time of 3.5 hours.
  • Range - the SOAR research aircraft has a maximum range of 1200 nautical miles.
  • Endurance - the SOAR research aircraft has an endurance of 5 hours at scientific payload.
  • Rate of climb – the climb capability of the SOAR research aircraft at ISA carrying the scientific payload is 2000 feet per minute.
  • Research power – The aircraft main power is connected to a main DC buss through a Cutler Hammer Relay, then to the Main Power Cable connected to a Power Distribution Rack Case which contains switch breakers for individual system components including de-icing power and 115V AC power. The research power available on the 28V DC supply is 6.7kW and on 115V AC supply is 1kW.
  • Hard points – The SOAR research aircraft is modified with two hard points (one per wing). The following design describes the specifications of each wing hard point:

    Maximum Weight: 60 pounds
    Center of Gravity: FS 137.0, BL 178.625
    Maximum Moment Arm to Wing Undersurface: 10.4 inches
    Equivalent Flat Plate Drag Area: 0.07 square feet

    Skin doublers in the wing undersurface and in the fuselage are designed for a variety of probes and an air inlet port for air sampling inside the pressurized cabin.
  • Crew – the aircraft crew consists of a pilot, a data system operator and up to two scientific observers. An instrument technician usually accompanies the crew in the field.
  • Research speed - the SOAR research aircraft has a research speed of 70 to 100 m/s. This speed can be adjusted to fulfill each research task.

Length from aft side of spar to aft side of seat rails: 75"
Length from aft side of seat rails to forward side of aft baggage: 28"
Aft baggage: L-30",W-39.5",H-42.5" forward and 36" at aft pressure bulkhead
Cabin: H-51",W-39.5" at floor level and 50" at arm rest level
Door: H-45" and W-27"
Instrument rack: L-32",W-19",H-40"
Width between seat rails (width between rows): 14.5"
Width between side of cabin and seat rail: 2" at floor level,4" at seven inches above the floor.

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