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weight and performance calculations for the Fokker F.IV (T-2)
Fokker F.IV (T-2)
role : passenger aircraft
importance : ***
first flight : operational : November 1922
design : Reinhold Platz
production : 2 aircraft built at Veere
general information :
Enlarged F.III with the pilot again seated besides the engine. The only 2 aircraft built were bought by the USAAS and were crated and shipped to the US. They were assembled at McCook Field and given designation T-2. The F.IV was to big for contemporary airlines and no more were sold. Lt. Oakley G. Kelly and Lt.John A. Macready started to make long distance flights with the T-2. Additional fuel tanks were installed. On 5 October 1922 they made the first attempt to cross the US coast to coast non-stop. Departing from San Diego, California they flew for 35 hours 18 minutes before fog forced them to land. On 3 November 1922 they tried again but now they had to land due to engine failure after 25 hours 30 minutes. On 16-17 April 1923 they made a duration flight in a closed circuit over Dayton, Ohio, being in the air for 36 hours 14 minutes. (average speed 112 km/hr > distance 4050 [km]) It was a new world duration record and also a distance record. On 2 May 1923 they made another attempt for the transcontinental flight. Now taking of from New York, they landed 26 hours 50 minutes later in San Diego, covering a distance of 4034 km. The aircraft is preserved in the National Air and Space Museum .
users : US Army Air Service
crew : 1 passengers : 12
engine : 1 Liberty L-12 liquid-cooled 12 -cylinder V-engine 400 [hp](298.3 KW)
dimensions :
wingspan : 24.79 [m], length : 14.79 [m], height : 3.6[m]
wing area : 89.0 [m^2]
weights :
max.take-off weight : 3640 [kg]
empty weight operational : 2250 [kg] useful load : 1000 [kg]
performance :
maximum speed :155 [km/hr] at sea-level
cruise speed :140 [km/u] op 100 [m]
service ceiling : 3000 [m]
range : 590 [km]
description :
parasol wing with fixed landing gear and tail strut
two spar wing
engines, landing gear attached to the fuselage, luggage compartment in the rear of the fuselage
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.65 [ ]
diameter airscrew 3.18 [m]
angle of attack prop : 13.30 [ ]
Max chord 14 ft 9 in = 4.50m span 81 ft 4.25in = 24.80m length : 49 ft 2.5in = 15.00m
Height : 11 ft 7.25in = 3.53m
reduction : 1.00 [ ]
airscrew revs : 1750 [r.p.m.]
pitch at Max speed 1.48 [m]
blade-tip speed at Vmax and max revs. : 247 [m/s]
calculation : *1* (dimensions)
measured wing chord : 3.88 [m]
mean wing chord : 3.59 [m]
calculated wing chord (rounded tips): 3.99 [m]
wing aspect ratio : 6.90 []
seize (span*length*height) : 1320 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 4.2 [kg/hr]
fuel consumption(cruise speed) : 75.1 [kg/hr] (102.4 [litre/hr]) at 73 [%] power
distance flown for 1 kg fuel : 1.86 [km/kg] at 1500 [m] cruise height, sfc : 345.0 [kg/kwh]
estimated total fuel capacity : 491.66 [litre] (360.39 [kg])
calculation : *3* (weight)
weight engine(s) dry : 383.0 [kg] = 1.28 [kg/KW]
John Arthur Macready & Oakley George Kelly standing before the T-2, fuel capacity increased to 735 gallon (2782 litres) > Standard fuel 130 gallon (492 litre) in the wing , added with a 410 gallon (1552 litre) tank to the wing centre section, and 185 gallon (700 litre) in the cabin. (10 gallon gravity tank ?? > 37.8 litre)
weight 31.1 litre oil tank : 2.64 [kg]
oil tank filled with 2.2 litre oil : 2.0 [kg]
oil in engine 16.6 litre oil : 14.9 [kg]
fuel in engine 2.0 litre fuel : 1.49 [kg]
weight 43.5 litre gravity patrol tank(s) : 6.5 [kg]
weight radiator : 42.7 [kg]
weight exhaust pipes & fuel lines 35.3 [kg]
weight self-starter : 7.3 [kg]
weight cowling 11.9 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 100.0 [kg]
total weight propulsion system : 605 [kg](16.6 [%])
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fuselage skeleton (steel tubes) : 5.53 [cm]): 357 [kg]
cabin layout : pitch : 87 [cm] (2+1) seating in 4.0 rows
weight 8.0 windows : 7.20 [kg]
passenger cabin width : 1.81 [m] cabin length : 3.48 [m] cabin height : 1.90 [m]
weight cabin furbishing : 28.81 [kg]
weight cabin floor : 40.42 [kg]
bracing : 37.2 [kg]
fuselage covering ( 41.3 [m2] doped linen fabric) : 12.8 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 8.2 [kg]
weight seats : 65.0 [kg]
weight 448 [litre] main fuel tank empty : 35.8 [kg]
2nd set of flight controls, so they could change places in flight. Bigger oval windows improved the view from the cabin when flying the aircraft from this location.
weight air conditioning : 18 [kg]
weight engine mounts & firewalls : 15 [kg]
total weight fuselage : 629 [kg](17.3 [%])
***************************************************************
weight plywood wing covering : 83 [kg]
total weight ribs (55 ribs) : 216 [kg]
load on front upper spar (clmax) per running metre : 601.7 [N]
load on rear upper spar (vmax) per running metre : 339.2 [N]
total weight 4 spars : 212 [kg]
weight wings : 512 [kg]
weight wing/square meter : 5.75 [kg]
weight cables (99 [m]) : 175.1 [kg] (= 1766 [gram] per metre)
diameter cable : 17.0 [mm]
weight fin & rudder (7.1 [m2]) : 42.1 [kg]
weight stabilizer & elevator (10.0 [m2]): 58.2 [kg]
total weight wing surfaces & bracing : 787 [kg] (21.6 [%])
*******************************************************************
Can only operate from paved runways
wheel pressure : 1820.0 [kg]
weight 2 wheels (860 [mm] by 132 [mm]) : 112.8 [kg]
weight tailskid : 5.6 [kg]
weight undercarriage with axle 47.0 [kg]
total weight landing gear : 165.3 [kg] (4.5 [%]
*******************************************************************
Endurance record : 35 hours, 18 minutes, 30 seconds (with average speed was 114 km/hr this would mean it flew over a distance of 4025 km !).
********************************************************************
calculated empty weight : 2186 [kg](60.1 [%])
weight oil for 5.1 hours flying : 21.2 [kg]
weight cooling fluids : 64.4 [kg]
calculated operational weight empty : 2272 [kg] (62.4 [%])
published operational weight empty : 2250 [kg] (61.8 [%])
***o***
"
weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 150 [kg]
********************************************************************
operational weight empty: 2503 [kg](68.8 [%])
weight 12 passengers : 924 [kg]
weight luggage & freight : 76 [kg]
operational weight loaded: 3503 [kg](68.8 [%])
fuel reserve : 137.0 [kg] enough for 1.83 [hours] flying
operational weight fully loaded : 3640 [kg] with fuel tank filled for 80 [%]
published maximum take-off weight : 3640 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 12.20 [kg/kW]
power loading (operational without useful load) : 8.39 [kg/kW]
total power : 298.3 [kW] at 1750 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.7 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 3.38 [hours]
design cycles : 1046 sorties, design hours : 3540 [hours]
operational wing loading : 276 [N/m^2]
wing stress (3 g) during operation : 144 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.21 ["]
max. angle of attack (stalling angle) : 12.68 ["]
angle of attack at max. speed : 1.76 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
lift coefficient at max. speed : 0.25 [ ]
induced drag coefficient at max. speed : 0.0037 [ ]
drag coefficient at max. speed : 0.0445 [ ]
drag coefficient (zero lift) : 0.0408 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded): 85 [km/u]
stalling speed at sea-level (MTOW): 86 [km/u]
landing speed at sea-level: 100 [km/hr]
min. drag speed (max endurance) : 109 [km/hr] at 1500 [m](power :54 [%])
flying weight : 3565 [kg]
min. power speed (max range) : 109 [km/hr] at 1500 [m] (power:54 [%])
max. rate of climb speed : 93.4 [km/hr] at sea-level
cruising speed : 140 [km/hr] op 1500 [m] (power:79 [%])
design speed prop : 147 [km/hr]
maximum speed : 155 [km/hr] op 100 [m] (power:107 [%])
climbing speed at sea-level : 254 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 103.3 [km/u]
static prop wash : 129 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level : 240 [m]
lift/drag ratio : 9.98 [ ]
climb to 1000m with max payload : 10.06 [min]
climb to 2000m with max payload : 27.05 [min]
climb to 3000m with max payload : 57.11 [min]
published ceiling (3000 [m]
practical ceiling (operational weight) : 5403 [m] with flying weight :2503 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 3298 [m] with flying weight :3602 [kg]
max. dive speed : 362.6 [km/hr] at 2298 [m] height
turning speed at CLmax : 108.5 [km/u] at 50 [m] height
turn radius at 50m: 45 [m]
time needed for 360* turn 9.3 [seconds] at 50m
load factor at max. angle turn 2.30 ["g"]
calculation *10* (action radius & endurance)
published range : 590 [km] with 1 crew and 969.7 [kg] useful load and 88.1 [%] fuel
range : 534 [km] with 1 crew and 1000.0 [kg] useful load and 79.7 [%] fuel
range : 452 [km] with 12.0 passengers with each 10 [kg] luggage and 67.5 [%] fuel
Available Seat Kilometres (ASK) : 5423 [paskm]
max range theoretically with additional fuel tanks for total 1756.1 [litre] fuel : 2391.8 [km]
useful load with range 500km : 1018 [kg]
useful load with range 500km : 10 passengers
Herman Hess in the cockpit of a F.IV. Hess was testpilot with Fokker, on 03 October 1925 he died while flying a military Fokker D.14 airplane at Schiphol. At a height of 300m he got in a spin and crashed.
production (useful load): 142.03 [tonkm/hour]
production (passengers): 1674.00 [paskm/hour]
short range airliner
oil and fuel consumption per tonkm : 0.56 [kg]
oil and fuel consumption per paskm : 0.05 [kg]
fuel cost per paskm : 0.05 [eur]
writing off per paskm : 0.27 [eur]
insurance per paskm : 0.01 [eur]
crew cost per paskm : 0.09 [eur]
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maintenance cost per paskm : 0.30 [eur]
direct operating cost per paskm : 0.72 [eur]
Literature :
Piston-engined airliners page 12
Praktisch handbook vliegtuigen deel 2 page 198
Van Spin tot Fokker 100 page 9,16,17
Fokker – bouwer aan de wereldluchtvaart page 55
Fokker verkeersvliegtuigen 1920-1940 page 18
Fokker verkeersvliegtuigen page 30,31
De Nederlandse vliegtuigen page 23
Fokkers “Roaring twenties” page 9,10
Vermetele vliegende Hollanders page 42
Alles over de Fokker Friendship page 20,21
Fokker F.IV Archives - This Day in Aviation
Fokker T-2 | Pioneers of Flight (si.edu)
Fokker T-2 | National Air and Space Museum (si.edu)
Fokker T2 | Aircraft | (fiddlersgreen.net)
Ogevallen/incidenten 1925 (hdekker.info)
DISCLAIMER Above calculations are based on published data, they must be
regarded as indication not as facts.
Calculated performance and weight may not correspond with actual weights
and performances and are assumptions for which no responsibility can be taken.
Calculations are as accurate as possible, they can be fine-tuned when more data
is available, you are welcome to give suggestions and additional information
so we can improve our program. For copyright on drawings/photographs/
content please mail to below mail address
T-2 flying over Rockwell field , San Diego California
To make a long-distance airplane out of the T-2, the of 11 passenger seats were removed, saving 55 kg. Weight of 2782 litre fuel tanks = 220 kg empty
(standard 492 litre tank = 36 kg) > additional weight : 184 kg
Stripping of passenger interior, will save weight. But the fuselage needed strengthening for the extra weight of the fuel tanks.
Empty weight + cooling fluids would be about 2550 kg + 160 kg weight crew +
Weight oil ( Pennzoil ) for 43 hours flight = 180 kg + 2782 litre fuel (2040 kg) > gives MTOW 4930 kg
TO distance with TO weight 4930 kg : 567 [m] stalling speed with weight 4930 kg : 100 km/hr ceiling with weight 4907 kg : 1408 [m] , with weight 2759 kg : 5108 [m]
Range of 4172 km at 116 km/hr at 49% power.
Wheel pressure with this TO weight is 2465 kg. With this high pressure it could only take off from a paved runway.
2516 miles = 4048 km in 26 hours 50 minutes = average ground speed 151 km/hr
(c) B van der Zalm 05 February 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4