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weight and performance calculations for the Fokker F.V
Fokker F.V
role : light passenger aircraft
importance : *
first flight : 07 December 1922 piloted by Herman Hess operational : not used operational
country : The Netherlands
design : Reinhold Platz
production : 1 prototype, built in Veere
general information :
The F.IV proved to be too big for the airlines, and thus Reinhold Platz designed a smaller airliner with seating for 8.
The F.V had an original concept; the lower wing could be easily detached to make a parasol-winged monoplane (wing area 45 m2) with higher cruise speed but lower flying weight (TOW 2655 kg max.speed 192 km/hr ). As a biplane (wing area 67.7 m2) it could carry more load (MTOW 3134 kg max.speed 180 km/hr ) but then with a lower cruise speed. Without bracing cables the loads on the lower wing would be mostly transferred to the upper wings via the struts. The fuselage was covered with plywood.
The passenger cabin was improved with heating from the exhaust pipe and a small toilet. The aircraft was no success and only one was built. Fokker himself flew the aircraft to try it but he was not satisfied with the aircraft and the behaviour in flight, being tail-heavy. It suffered from vibrations of the plywood sheets and the noise in the passenger cabin was deafening according to aviation journalist Henri Hegener, a good friend of Anthony Fokker. It was not used in service on scheduled passenger flights. It made an demonstration flight to Moscow, Russia and was tried for two weeks by the German-Russia Deruluft company with registration RR13. There were problems with maintenance and the detachable wing and no orders followed.
Most of the time it was flown as a biplane. It had dual control for the two crew.
It led to disagreement between Anthony Fokker and Reinhold Platz working in Veere, and Fokker gave Rethel , working in Amsterdam Noord (former ELTA exhibition sheds), the appointment to design the next passenger aircraft, resulting in the successful F.VII.
The steal frame of the fuselage needed inspection every 50 hours, but this was not easy done due to the two-layer plywood covering.
Later it was sold to an Austria airline, the Oesterreichische Luftverkehrs AG (Oelag), but what happened with the aircraft is not known, no registration was given in Austria.
Cabin height : 1.80 [m]
Registrations : H-NABW, RR-13
users : Oelag ?
crew : 2 passengers : 8
engine : 1 Rolls Royce Eagle VIII liquid-cooled 12 -cylinder V-engine 360 [hp](268.5 KW)
Now with the lower wing removed. The idea was to convert it into a high speed air taxi.
Weight lower wing (22.7m2) about 135 kg. Weight of the N-struts ca. 30 kg. This gives an empty weight of 1900-135-30 = about 1735 kg in this configuration.
With one wing (45m2) and TOW 2655 [kg] it had a very high wing loading of 579 [N/m2] , average wing loading at this time was about 425 [N/m2]. The high wing loading gave a stalling speed of 103 km/hr and a TO distance of 815m ! ceiling loaded weight : 2300 [m] range : 350 km with 7 passengers. Max .passengers : 7
dimensions :
wingspan : 16.26 [m], length : 12.0 [m], height : 4.0[m]
wing area : 67.7 [m^2]
weights :
max.take-off weight : 3134 [kg]
empty weight operational : 1900 [kg] useful load : 800 [kg]
performance :
maximum speed :178 [km/hr] at sea-level
cruise speed :160 [km/u] op 100 [m]
service ceiling : 3000 [m]
range : 900 [km]
description :
1-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
engines, landing gear attached to the fuselage, luggage compartment in the rear of the fuselage
airscrew :
fixed pitch 4 -bladed tractor airscrew with max. efficiency :0.59 [ ]
estimated diameter airscrew 3.00 [m]
angle of attack prop : 23.15 [ ]
reduction : 0.62 [ ]
airscrew revs : 1178 [r.p.m.]
pitch at Max speed 2.52 [m]
blade-tip speed at Vmax and max revs. : 162 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.22 [m]
mean wing chord : 2.08 [m]
calculated wing chord (rounded tips): 2.28 [m]
wing aspect ratio : 7.81 []
estimated gap : 1.97 [m]
gap/chord : 0.95 [ ]
seize (span*length*height) : 780 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 4.8 [kg/hr]
fuel consumption(cruise speed) : 62.8 [kg/hr] (85.7 [litre/hr]) at 69 [%] power
distance flown for 1 kg fuel : 2.55 [km/kg] at 1500 [m] cruise height, sfc : 337.0 [kg/kwh]
estimated total fuel capacity : 546.16 [litre] (400.33 [kg])
calculation : *3* (weight)
weight engine(s) dry : 379.0 [kg] = 1.41 [kg/KW]
weight reduction gear : 29.5 [kg]
weight 43.0 litre oil tank : 3.65 [kg]
oil tank filled with 2.0 litre oil : 1.8 [kg]
oil in engine 15.0 litre oil : 13.4 [kg]
fuel in engine 1.8 litre fuel : 1.34 [kg]
weight 36.4 litre gravity patrol tank(s) : 5.5 [kg]
weight radiator : 38.5 [kg]
weight exhaust pipes & fuel lines 33.0 [kg]
weight self-starter : 6.6 [kg]
weight cowling 10.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 111.1 [kg]
total weight propulsion system : 660 [kg](21.1 [%])
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cabin layout : pitch : 87 [cm] (1+1) seating in 4.0 rows
weight toilet : 5 [kg]
weight 8.0 windows : 7.20 [kg]
passenger cabin width : 1.51 [m] cabin length : 3.48 [m] cabin height : 1.80 [m]
weight cabin furbishing : 20.51 [kg]
weight cabin floor : 33.53 [kg]
bracing : 11.6 [kg]
fuselage covering ( 27.2 [m2] plywood 3 mm) : 49.7 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight dual controls + indicators: 16.2 [kg]
weight seats : 50.0 [kg]
weight 510 [litre] main fuel tank empty : 40.8 [kg]
weight air conditioning : 12 [kg]
weight engine mounts & firewalls : 13 [kg]
total weight fuselage : 537 [kg](17.1 [%])
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weight plywood wing covering : 60 [kg]
total weight ribs (123 ribs) : 186 [kg]
load on front upper spar (clmax) per running metre : 1027.7 [N]
load on rear upper spar (vmax) per running metre : 527.2 [N]
Registration RR13 applied for a promotion tour to Moscow. Picture taken at Schiphol ?
total weight 8 spars : 156 [kg]
weight wings : 402 [kg]
weight wing/square meter : 5.94 [kg]
weight 4 interplane struts & cabane : 38.5 [kg]
weight fin & rudder (3.1 [m2]) : 18.7 [kg]
weight stabilizer & elevator (7.6 [m2]): 45.8 [kg]
total weight wing surfaces & bracing : 524 [kg] (16.7 [%])
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wheel pressure : 1567.0 [kg]
weight 2 wheels (930 [mm] by 143 [mm]) : 76.3 [kg]
weight tailskid : 5.3 [kg]
weight undercarriage with axle 52.1 [kg]
total weight landing gear : 133.7 [kg] (4.3 [%]
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calculated empty weight : 1855 [kg](59.2 [%])
weight oil for 6.7 hours flying : 32.6 [kg]
weight cooling fluids : 58.0 [kg]
calculated operational weight empty : 1946 [kg] (62.1 [%])
published operational weight empty : 1900 [kg] (60.6 [%])
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weight crew : 162 [kg]
On the left Henri Hegener , the first Dutch aviation journalist, in the middle Friedrich Seekatz , head of the Fokker sales department, and to the right Cis van Rhijn , Fokker’s secretaresse in the cabin of the F.V on its way to Moscow for a promotional tour. Journalist Hegener was denied access to Russia and had to leave the party in Berlin.
weight fuel for 2.0 hours flying : 126 [kg]
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operational weight empty: 2233 [kg](71.3 [%])
weight 8 passengers : 616 [kg]
weight luggage & freight : 184 [kg]
operational weight loaded: 3033 [kg](71.3 [%])
fuel reserve : 100.7 [kg] enough for 1.60 [hours] flying
operational weight fully loaded : 3134 [kg] with fuel tank filled for 57 [%]
published maximum take-off weight : 3134 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 11.67 [kg/kW]
power loading (operational without useful load) : 8.32 [kg/kW]
total power : 268.5 [kW] at 1900 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.1 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.5 [g]
High stalling speed (91 km/hr) and long TO distance : 485m
design flight time : 3.93 [hours]
design cycles : 814 sorties, design hours : 3200 [hours]
operational wing loading : 324 [N/m^2]
wing stress (3 g) during operation : 163 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.17 ["]
max. angle of attack (stalling angle) : 12.31 ["]
angle of attack at max. speed : 1.39 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max. speed : 0.22 [ ]
induced drag coefficient at max. speed : 0.0034 [ ]
drag coefficient at max. speed : 0.0312 [ ]
drag coefficient (zero lift) : 0.0278 [ ]
calculation : *8* (speeds
stalling speed at sea-level (MTOW): 91 [km/u]
landing speed at sea-level: 106 [km/hr]
min. drag speed (max endurance) : 133 [km/hr] at 1500 [m](power :63 [%])
min. power speed (max range) : 133 [km/hr] at 1500 [m] (power:63 [%])
max. rate of climb speed : 110.1 [km/hr] at sea-level
cruising speed : 160 [km/hr] op 1500 [m] (power:82 [%])
design speed prop : 169 [km/hr]
maximum speed : 178 [km/hr] op 100 [m] (power:108 [%])
climbing speed at sea-level : 215 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 109.8 [km/u]
static prop wash : 91 [km/u]
take-off distance at sea-level : 485 [m]
lift/drag ratio : 11.15 [ ]
climb to 1000m with max payload : 14.48 [min]
climb to 1500m with max payload : 28.70 [min]
climb to 2000m with max payload : 64.25 [min]
practical ceiling (operational weight) : 3843 [m] with flying weight :2233 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 2228 [m] with flying weight :3103 [kg]
calculation *10* (action radius & endurance)
published range : 900 [km] with 2 crew and 673.5 [kg] useful load and 88.1 [%] fuel
range : 577 [km] with 2 crew and 800.0 [kg] useful load and 56.5 [%] fuel
range : 843 [km] with 8.0 passengers with each 10 [kg] luggage and 82.5 [%] fuel
Available Seat Kilometres (ASK) : 6741 [paskm]
max range theoretically with additional fuel tanks for total 1510.6 [litre] fuel : 2825.3 [km]
useful load with range 500km : 911 [kg]
useful load with range 500km : 8 passengers
production (useful load): 145.99 [tonkm/hour]
production (passengers): 1281.60 [paskm/hour]
oil and fuel consumption per tonkm : 0.46 [kg]
oil and fuel consumption per paskm : 0.05 [kg]
fuel cost per paskm : 0.05 [eur]
writing off per paskm : 0.34 [eur]
insurance per paskm : 0.01 [eur]
crew cost per paskm : 0.12 [eur]
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maintenance cost per paskm : 0.30 [eur]
direct operating cost per paskm : 0.82 [eur]
Literature :
Wikipedia
Fokker verkeersvliegtuigen page 34,35,36,37
Fokker verkeersvliegtuigen 1920-1940 page 19,78
Fokker bouwer aan de wereldluchtvaart page 57
Van Spin tot Fokker 100 page 19
De Nederlandse vliegtuigen page 32
Alles over de Fokker Friensdhip page 16, 21, 22
www.dutch-aviation.nl/index5/Civil/index5-2 F5.html (dutch-aviation.nl)
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
(c) B van der Zalm 16 March 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4