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METRO II - NLR aircraft

Status: Not defined
Publication State:


METRO II - NLR is a medium tropospheric research aircraft operated by Nationaal Lucht- en Ruimtevaartlaboratorium, NLR, The Netherlands.

Abbreviation: metro, II, -, NLR
Keywords: Not defined

platformType:      aircraft
location:      None
Previously used record indentifiers:

More Information (under review)

Dimensions: Length: 18.09 m; Height: 5.06 m; Wingspan: 14.10 m; Flying performances: Speed: Min speed: 33 m/s Max speed: 128 m/s Usual speed during measurements: 100 m/s Usual speed during transit flights: 128 m/s Ascent rate: 2400 m/s Altitude: (1 ft = 0.31 m) Min altitude: Above sea: 1640 ft Above ground: 1640 ft Max ceiling: 25000 ft Usual ceiling during measurements: 20000 ft Ceiling limitations: To be defined. Payload: Empty weight: 4080 kg Max take-off weight: 5670 kg Max payload: 1450 kg Usual scientific payload during measurements: 1350 kg Endurance: Max endurance: 6 h (at min scientific payload and max fuel) (Y-coordinate of 1st point) Endurance at max scientific payload: 4 h ... (Y-coordinate of 2nd point) Range: Max range: 2300 km (at min scientific payload and max fuel) Conditions for max range: Minimu crew, landing gear retracted with cruise altitude : 20000 ft with 2450 kg fuel with 70 kg payload Range at max scientific payload: 880 km Other: Weather conditions limitations: IFR, VFR, Approved for flight into known icing conditions Take-off runway length: 800 m Engines: AiResearch TPE 331-3UW-304G engines, producing 625 kW (840 SHP) continuously and 700 kW (940 SHP) with water injection.; Avionics: The aircraft is equipped with all required civil communication, navigation and avionics systems, GPS, and a flight Director/Autopilot. - Programmable Electronic Flight Instrument System (EFIS) in right instrument panel. - Research flight management system - Highly accurate position reference system (cm accuracy) - Test equipment control panel - Special electrical system to feed test equipment - Numerous adaptations in cockpit and cabin to accomodate test equiment Crew and scientists on board: Crew (pilots + operators): 2 pilots1 test flight engineer in case of standart experiments.; Seats available for scientists: 6 Cabin: Length: 10.09 m Width: max : 1.50 mfloor: 1.13 m Height: 1.46 m Apertures: Entrance door, left forward fuselage Size : width : 0.64 m Cargo door : left side : 1.345 x 1.3 Emergency overwing exits : 2 right side, 1 left side; Cabin pressurized: 7 PSI max More information: Cabine Volume : 17 m3; Aircraft modifications: Nose boom: length : 2.3 m Windows: 9 left hand side (with sun shades) 10 right hand side (with sun shades) Openings: - A 0.61 m x 0.61 m camera hatch with 40 mm optical glass, which can be replaced by metal plates for mounting special equipment (e;g; antennas, trailing static tube). -Opening in bottom fuselage at copilots seat for navigation sights Hard points: Hard point under fuselage at wing intersection (max load 160 kg) for an instrumentation pod, antennas or other equipment. Antenna support on the top of the fuselage. Additionnal systems: Numerous facilities in the cabin and cockpit for accomodating test equipment A "roof rack" can be installed on top of the fuselage that can accomodate multiple antennas. Acquisition systems: A multi-channel digital data acquisition and recording system that can handle a large number of parameters with high accuracy at a high sample rate is installed. Electrical power: Aircraft total electrical power (kW): 2 x 300 A , 28 VDC Electrical power (kW) and voltages (V) available for scientists: A separate electrical system dedicated to powering on-board test equipment, (28 VDC, 115 VAC 400 Hz, 220 VAC)Total available for experiments : 300 A, 28 VDC

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