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