MOUNTAIN GOAT STOL™
High Performance Bush Plane and General Aviation Aircraft
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3.  MOUNTAIN GOAT STOL™ SPECIFICATIONS AND PERFORMANCE
MOUNTAIN GOAT STOL™ in the altitudes of Alaska.
MOUNTAIN GOAT STOL™ in the altitudes of Alaska.
SPECIFICATIONS
Power Plant: Lycoming IO 360 B2E, 180 HP, 2000 hr TBO
Propeller: McCauley fixed pitch 76-66
Length: 24.3 ft
Height: 6.75 ft
Wing Span: 35.5 ft
Wing Area: 188 sq ft
Seats: 2 Tandem
Empty Weight: 1,250 lbs w 4130 Chrome Moly alloy airframe; 1,170 lbs w Titanium airframe
Max Gross Weight: 2,500 lbs
Useful Load as tested: 1,250 lbs w 4130 Chrome Moly alloy airframe; 1,330 lbs w Titanium airframe
Payload with full fuel as tested: 830 lbs w 4130 Chrome Moly alloy airframe; 910 lbs w Titanium airframe
Fuel capacity, standard total / usable: 65 US gallons / 62 US Gallons
Baggage Area VOLUME (behind rear seat): 32 cu ft
Baggage Area, MAXIMUM WEIGHT: 350 lbs w 4130 Chrome Moly alloy airframe; 430 lbs w Titanium airframe
Montagne MOUNTAIN GOAT STOL™ in California.
Montagne MOUNTAIN GOAT STOL™ in California.
PERFORMANCE

Rather than optimize the aircraft configuration to present the highest possible performance figures, which are not attainable in a typically configured aircraft, cited MOUNTAIN GOAT STOL™ performance figures are derived from a real world, working configuration, typical for the bush pilot.

MOUNTAIN GOAT STOL™ DATA2 WITH 26-INCH DIAMETER × 10.5 × 6 GOODYEAR TUNDRA TIRES.
Takeoff max performance w light load: 50 ft
Takeoff max performance @ max gross weight (with full useful load of 1,250 lbs w 4130 Chrome Moly alloy airframe; 1,330 lbs w Titanium airframe): 300 ft
Max demonstrated X wind: 26 mph
Rate of climb, sea level w light load: 2,200 fpm
Rate of climb, sea level @ max gross weight (with full useful load of 1,250 lbs w 4130 Chrome Moly alloy airframe; 1,330 lbs w Titanium airframe): 1,200 fpm
Cruise speed / endurance with 45 minute reserve @ 100 mph: 1,400 statute miles
Cruise speed / endurance with 45 minute reserve @ 155 mph: 800 statute miles
@75% Power 2,200 lbs 5,000 ft: 159 mph1
@75% Power 1,670 lbs 5,000 ft: 152 mph1
@55% Power SEA LEVEL 128 mph
Landing distance, ground roll @ 1,670 lbs: 120 ft
Landing distance, ground roll @ 2,475 lbs: 275 ft
Vx 55 mph
Vy 75 mph
Va 120 mph
Vs1 @ 1,900 lbs — Flaps Reflexed: 50 mph
Vs0 @ 1,900 lbs: 32 mph
Vs0 @ 1,670 lbs: 27 mph
 



1.  To fly with a neutral pitch with massive aft CG loads, the airfoil has a designed pitching moment which unloads the tail as aircraft total weight increases. This results in the need to apply aerodynamic force (up elevator) at lighter loads to compensate for the pitching moment, which results in turn in higher drag and lower cruising speeds at light loads.


2.  Performance data pending FAA certification.