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weight and performance calculations for the Fokker D.VI

Fokker D.VI

role : fighter

importance : **

first flight : operational : April 1918

country : Germany

design : Reinhold Platz

production : 56 aircraft

general information :

general information :

Due to lack of castor oil the Ur.II rotary engines did not perform well. Production was slow as priority was given to the production of the D.VII. Production was stopped in August 1918 after only 56 aircraft had been built. Only a few reached front-line units, Jasta 84 was one of them. The remaining went to fighter-pilot training units. It had good performance but was over classed by the D.VII and later the D.VIII.

users : Luftwaffe, Austro-Hungaria (7)

crew : 1

armament : 2 synchronized 7.92 [mm] (0.312 in) Spandau LMG 08/15 machine-guns

engine : 1 Oberursel UR.II air-cooled 9 -cylinder two-valve rotary engine 110 [hp]

(82.0 KW)

dimensions :

wingspan : 7.65 [m], length : 6.23 [m], height : 2.55[m]

wing area : 17.7 [m^2]

weights :

max.take-off weight : 583 [kg]

empty weight operational : 393 [kg] bombload : 0 [kg]

performance :

maximum speed : 196 [km/hr] at sea-level

service ceiling : 6000 [m]

endurance : 1.5 [hours]

estimated action radius : 132 [km]

description :

1-bay biplane with fixed landing gear and tail strut

two spar upper and lower wing

engines, landing gear, fuel and bombs in or attached to the fuselage

airscrew :

fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.64 [ ]

diameter airscrew 2.62 [m]

angle of attack prop : 25.69 [ ]

coarse pitch

reduction : 1.00 [ ]

airscrew revs : 1100 [r.p.m.]

pitch at Max speed 2.97 [m]

blade-tip speed at Vmax and max revs. : 160 [m/s]

Afbeeldingsresultaat voor Fokker D.VI

calculation : *1* (dimensions)

mean wing chord : 1.16 [m]

calculated wing chord (rounded tips): 1.32 [m]

wing aspect ratio : 6.61 []

estimated gap : 1.33 [m]

gap/chord : 1.15 [ ]

seize (span*length*height) : 122 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 6.2 [kg/hr]

fuel consumption(cruise speed) : 21.0 [kg/hr] (28.7 [litre/hr]) at 68 [%] power

distance flown for 1 kg fuel : 8.39 [km/kg]

estimated total fuel capacity : 49 [litre] (36 [kg])

calculation : *3* (weight)

weight engine(s) dry : 151.7 [kg] = 1.85 [kg/KW]

weight 14 litre oil tank : 1.8 [kg]

oil tank filled with 0.6 litre oil : 0.6 [kg]

oil in engine 0 litre oil : 0.4 [kg]

fuel in engine 1 litre fuel : 0.4 [kg]

weight 12 litre gravity patrol tank(s) : 1.2 [kg]

weight cowling 3.3 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]

total weight propulsion system : 177 [kg](30.3 [%])

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fuselage skeleton (wood gauge : 4.70 [cm]): 35 [kg]

bracing : 1.6 [kg]

fuselage covering ( 7.3 [m2] doped linen fabric) : 2.3 [kg]

Afbeeldingsresultaat voor Fokker D.VI

weight controls + indicators: 5.2 [kg]

weight seats : 3.0 [kg]

weight other details, lighting set, etc. : 5.1 [kg]

weight 37 [litre] main fuel tank empty : 3.5 [kg]

weight engine mounts & firewalls : 4 [kg]

total weight fuselage : 60 [kg](10.3 [%])

***************************************************************

weight wing covering (doped linen fabric) : 11 [kg]

total weight ribs (41 ribs) : 35 [kg]

load on front upper spar (clmax) per running metre : 578.5 [N]

load on rear upper spar (vmax) per running metre : 222.3 [N]

total weight 8 spars : 19 [kg]

weight wings : 65 [kg]

weight wing/square meter : 3.69 [kg]

weight 4 interplane struts & cabane : 6.1 [kg]

weight cables (39 [m]) : 1.2 [kg] (= 31 [gram] per metre)

diameter cable : 2.2 [mm]

weight fin & rudder (0.7 [m2]) : 2.6 [kg]

weight stabilizer & elevator (2.0 [m2]): 7.5 [kg]

total weight wing surfaces & bracing : 83 [kg] (14.2 [%])

*******************************************************************

weight machine-gun(s) : 34.0 [kg]

weight ammunition magazine(s) :3.5 [kg]

weight Fokker Zentralsteuerung synchronization gear : 2.0 [kg]

weight armament : 40 [kg]

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wheel pressure : 291.5 [kg]

weight 2 wheels (710 [mm] by 85 [mm]) : 14.2 [kg]

weight tailskid : 1.3 [kg]

weight undercarriage with axle 15.0 [kg]

total weight landing gear : 30.5 [kg] (5.2 [%]

*******************************************************************

Fokker D.VI

********************************************************************

calculated empty weight : 389 [kg](66.8 [%])

weight oil for 1.8 hours flying : 11.1 [kg]

weight ammunition (1000 rounds) : 28.2 [kg]

weight signal pistol with cartridges : 3.6 [kg]

weight automatic pistol with spare magazines : 1.2 [kg]

*******************************************************************

calculated operational weight empty : 434 [kg] (74.4 [%])

published operational weight empty : 393 [kg] (67.4 [%])

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weight crew : 81 [kg]

weight fuel for 1.5 hours flying : 32 [kg]

********************************************************************

operational weight : 546 [kg](93.7 [%])

estimated bomb load : 25 [kg]

operational weight bombing mission : 571 [kg]

fuel reserve : 4 [kg] enough for 0.20 [hours] flying

possible additional useful load : 8 [kg]

operational weight fully loaded : 583 [kg] with fuel tank filled for 100 [%]

published maximum take-off weight : 583 [kg] (100.0 [%])

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calculation : * 4 * (engine power)

power loading (operational without bombload) : 6.66 [kg/kW]

total power : 82.0 [kW] at 1100 [r.p.m]

Afbeeldingsresultaat voor Fokker D.VI

calculation : *5* (loads)

manoeuvre load : 4.2 [g] at 1000 [m]

limit load : 4.5 [g] ultimate load : 6.8 [g] load factor : 2.0 [g]

design flight time : 1.20 [hours]

design cycles : 292 sorties, design hours : 350 [hours]

operational wing loading : 303 [N/m^2]

wing stress (3 g) during operation : 246 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -2.09 ["]

max. angle of attack (stalling angle) : 12.44 ["]

angle of attack at max. speed : -0.02 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° :0.17 [ ]

lift coefficient at max. angle of attack : 1.18 [ ]

lift coefficient at max. speed : 0.17 [ ]

induced drag coefficient at max. speed : 0.0024 [ ]

drag coefficient at max. speed : 0.0302 [ ]

drag coefficient (zero lift) : 0.0278 [ ]

calculation : *8* (speeds

stalling speed at sea-level (OW): 74 [km/u]

landing speed at sea-level (OW without bombload): 88 [km/hr]

min. drag speed (max endurance) : 123 [km/hr] at 3000 [m](power :39 [%])

min. power speed (max range) : 128 [km/hr] at 3000 [m] (power:40 [%])

max. rate of climb speed : 117.8 [km/hr] at sea-level

cruising speed : 176 [km/hr] op 3000 [m] (power:62 [%])

design speed prop : 190 [km/hr]

maximum speed : 196 [km/hr] op 100 [m] (power:100 [%])

climbing speed at sea-level (without bombload) : 307 [m/min]

calculation : *9* (regarding various performances)

take-off distance at sea-level : 33 [m]

lift/drag ratio : 10.25 [ ]

max. practical ceiling : 6525 [m] with flying weight :492 [kg]

practical ceiling (operational weight) : 5950 [m] with flying weight :546 [kg] line 3385

practical ceiling fully loaded (mtow- 1 hour fuel) : 5800 [m] with flying weight :562 [kg]

published ceiling (6000 [m]

RODEN 007 FOKKER D.VI - grootste modelbouwwinkel van Europa

climb to 1500m (operational weight without bombload) : 4.86 [min]

climb to 3000m (operational weight without bombload) : 10.95 [min]

climb to 5000m : 25.15 [min] climbing speed at 5000m :106 [m/min]

max. dive speed : 454.6 [km/hr] at 4800 [m] height

load factor at max. angle turn 2.13 ["g"]

turn radius at 500m: 51 [m]

time needed for 360* turn 10.4 [seconds] at 500m

calculation *10* (action radius & endurance)

operational endurance : 1.70 [hours] with 1 crew and 33 [kg] useful (bomb)load and 100.0 [%] fuel

published endurance : 1.50 [hours] with 1 crew and possible useful (bomb) load : 37 [kg] and 88.1 [%] fuel

action radius : 203 [km] with 1 crew and 20[kg] photo camera or bombload

max range theoretically with additional fuel tanks for total 138 [litre] fuel : 851 [km]

useful load with action-radius 250km : 42 [kg]

production : 7.38 [tonkm/hour]

oil and fuel consumption per tonkm : 3.68 [kg]

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Literature :

fighters 1914-19 page 65

Wikipedia

German aircraft of the first world war page 105

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/

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(c) B van der Zalm 24 June 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4