HondaJet Backgrounder

9/25/2007 6:00:00 AM

HondaJet is an advanced light jet with revolutionary technology and design attributes that help it achieve far better fuel efficiency, more available cabin and luggage space, and higher cruise speed than conventional aircraft in its class.
HondaJet Innovation:
  • A patented over-the-wing engine-mount (OTWEM) configuration was developed using advanced concepts in aerodynamics and design simulation. The OTWEM configuration eliminates the carry-through structure of conventional fuselage-mount designs, allowing for greater use of fuselage space for the cabin and cargo areas. The configuration is also expected to reduce cabin noise. Through optimization of the design and placement of the engine nacelles, the OTWEM configuration actually exhibits less drag at high speeds than conventional "clean wing" designs, contributing significantly to HondaJet's superior performance and fuel efficiency.
  • A natural-laminar flow (NLF) wing and NLF fuselage nose were developed through extensive analyses and wind tunnel testing. These designs help achieve lower aerodynamic drag at high speeds together with a high lift coefficient.
  • An advanced all-composite fuselage structure, consisting of a unique combination of honeycomb sandwich and stiffened panels structures joined using a patented integral co-curing process, reduces weight for optimal performance and payload capacity, while also reducing manufacturing complexity.
  • An advanced, all-glass cockpit utilizes the next-generation of the Garmin G1000 avionics platform with features and capabilities unique to the HondaJet.
Milestone Achievements:
HondaJet was designed and developed by Honda engineers working in the U.S. and Japan. Research work that led to the creation of HondaJet began in 1986. The jet was constructed by Honda R&D Americas in Greensboro, North Carolina, and all flight tests have been conducted in the U.S. Honda Aircraft Company, Inc., headquartered in Greensboro, was established in October 2006 to oversee certification, production and sales of HondaJet.
  • Major ground tests including structural proof tests, control-system proof test, system function tests and ground vibration tests were completed in December 2003.
  • HondaJet made its first flight on Dec. 2, 2003
  • HondaJet has recorded more than 330 flight hours through September 2007
  • Application for FAA type-certification was made on October 11, 2006
Basic Design Specifications:
Maximum Cruise Speed @ FL300 420KTAS
Service Ceiling FL430
Pressurization (Differential) 8.7psi
Range Performance:
VFR Range (Maximum fuel with available payload - 644lbs) 1400nm
NBAA IFR Range (Cruise@FL410, Alternate 100nm, 45 minute reserve, 1 Pilot plus 3 Passengers) 1180 nm
Rate of Climb 3990 ft/min
Airport Performance:
Take-off Distance (distance required to climb to 35 feet above the runway plus a 15% factor) 3120 ft
Landing Distance
2500 ft
Manufacturer / Model GE HONDA / HF120 (x2)
Output 1880 lb/each (Max Take-Off)
Bypass Ratio 2.9
External Dimensions:
Height 13.21 ft (4.03 m)
Length 41.70 ft (12.71 m)
Span 39.87 ft (12.15 m)
Cabin Dimensions:
Height 4.94 ft (1.51 m)
Length (fwd. pressure bulkhead to aft pressure bulkhead 17.80 ft (5.43 m)
Width 5.00 ft (1.52 m)
Typical 2 crews + 5 passengers (or 1 crew + 6 passengers)
Air taxi 2 crews + 6 passengers
Baggage Capacity:
Nose Baggage 9 cubic feet.
Aft Baggage 57 cubic feet