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Fokker M.5L (A.II)

Anthony Fokker in a A.II

Fokker M.5L (A.II)

role : single seat scout

first flight : operational : may 1914

country : Germany

design : Fokker & Martin Kreutzer

production : 20 aircraft

general information :

Short before WWI Fokker had bought a second hand Morane Saulnier H which had better flying qualities then his own Spin aircraft.

Fokker had seen the Frenchman Pegoud performing looping’s in his Bleriot XIbis in the autumn of 1913 and other aerobatics with could not be done with his Spin.

The Morane H formed the basis for the M.5 in which Fokker replaced the wooden frame for welded steel tubes for the fuselage. It used a 80 hp Gnome Lambda 7-cil. Rotary engine, built under license by Oberursel as U.0.

As on the Morane it used all-moving tail planes. It could perform aerobatics although it was very light on the controls. Fokker did those aerobatics himself in May and June 1914 and won some prices with it. Fokker built two versions the M.5L with increased span wings and the M.5K with short wings. The German Signal Corps ordered 20 to 24 M.5L aircraft given the military indication A.II and used as light scout plane. After the outbreak of WWI the German needed more airplanes. They ordered at the beginning of 1915 10 Fokker M.5K aircraft, military indication A.III. During the initial production Fokker developed the synchronizing system for the machine gun. The first 5 M.5K’s were fitted with the synchronized machine gun, designated as M.5K/MG. In military service they were indicated as E.I and formed the start of the Fokker scourge.

users : Luftwaffe

crew : 1

armament : no fixed armament

engine : 1 Oberursel U.O air-cooled 7 -cylinder atmospheric inlet-valve rotary engine 80 [hp](58.8 KW)

dimensions :

wingspan : 9.5 [m], length : 7.2 [m], height : 2.75[m]

wing area : 16.0 [m^2]

weights :

max.take-off weight : 510 [kg]

empty weight operational : 340 [kg] bombload : 0 [kg]

performance :

maximum speed : 130 [km/hr] at sea-level

service ceiling : 3000 [m]

estimated action radius : 162 [km]

Demonstratie van de sterkte van een M.5L

description :

shoulder-winged monoplane with fixed landing gear and tail strut

two spar wing

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

airscrew :

fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.62 [ ]

estimated diameter airscrew 2.32 [m]

angle of attack prop : 18.28 [ ]

reduction : 1.00 [ ]

airscrew revs : 1200 [r.p.m.]

pitch at Max speed 1.81 [m]

blade-tip speed at Vmax and max revs. : 150 [m/s]

calculation : *1* (dimensions)

mean wing chord : 1.68 [m]

calculated wing chord (rounded tips): 2.16 [m]

wing aspect ratio : 5.64 []

gap : 0.00 [m]

gap/chord : 0.00 [ ]

seize (span*length*height) : 188 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 6.5 [kg/hr]

fuel consumption(cruise speed) : 21.6 [kg/hr] (29.5 [litre/hr]) at 72 [%] power

distance flown for 1 kg fuel : 5.41 [km/kg]

estimated total fuel capacity : 93 [litre] (68 [kg])

calculation : *3* (weight)

weight engine(s) dry : 116.5 [kg] = 1.98 [kg/KW]

weight 26 litre oil tank : 2.2 [kg]

oil tank filled with 0.4 litre oil : 0.4 [kg]

oil in engine 0 litre oil : 0.3 [kg]

fuel in engine 0 litre fuel : 0.3 [kg]

weight 13 litre gravity patrol tank(s) : 1.9 [kg]

weight cowling 2.4 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 13.5 [kg]

total weight propulsion system : 135 [kg](26.5 [%])

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fuselage skeleton (wood gauge : 4.84 [cm]): 43 [kg]

bracing : 2.2 [kg]

fuselage covering ( 9.8 [m2] doped linen fabric) : 3.1 [kg]

weight controls + indicators: 5.7 [kg]

weight seats : 3.0 [kg]

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

weight 80 [litre] main fuel tank empty : 6.4 [kg]

weight engine mounts & firewalls : 3 [kg]

total weight fuselage : 72 [kg](14.0 [%])

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

weight wing covering (doped linen fabric) : 10 [kg]

total weight ribs (25 ribs) : 30 [kg]

load on front upper spar (clmax) per running metre : 462.1 [N]

load on rear upper spar (vmax) per running metre : 147.1 [N]

total weight 4 spars : 24 [kg]

weight wings : 64 [kg]

weight wing/square meter : 4.03 [kg]

weight cables (38 [m]) : 7.6 [kg] (= 199 [gram] per metre)

diameter cable : 5.7 [mm]

weight fin & rudder (1.0 [m2]) : 4.4 [kg]

weight stabilizer & elevator (1.8 [m2]): 7.4 [kg]

total weight wing surfaces & bracing : 84 [kg] (16.4 [%])

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weight armament : 0 [kg]

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wheel pressure : 255.0 [kg]

weight 2 wheels (660 [mm] by 79 [mm]) : 11.8 [kg]

weight tailskid : 1.4 [kg]

weight undercarriage with axle 16.6 [kg]

total weight landing gear : 29.7 [kg] (5.8 [%]

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

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calculated empty weight : 320 [kg](62.8 [%])

weight oil for 3.3 hours flying : 21.6 [kg]

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Fokker flying school at Doberitz, tot he right a Fokker M.5, to the left a M.1 Spin

calculated operational weight empty : 342 [kg] (67.0 [%])

published operational weight empty : 340 [kg] (66.7 [%])

---o---

weight crew : 81 [kg]

weight fuel for 2.0 hours flying : 43 [kg]

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

operational weight : 466 [kg](91.4 [%])

estimated bomb load : 25 [kg]

operational weight bombing mission : 491 [kg]

fuel reserve : 19 [kg] enough for 0.87 [hours] flying

operational weight fully loaded : 510 [kg] with fuel tank filled for 91 [%]

published maximum take-off weight : 510 [kg] (100.0 [%])

I||==|

calculation : * 4 * (engine power)

power loading (operational without bombload) : 7.92 [kg/kW]

total power : 58.8 [kW] at 1200 [r.p.m]

calculation : *5* (loads)

manoeuvre load : 1.8 [g] at 1000 [m]

limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.4 [g]

design flight time : 2.22 [hours]

design cycles : 450 sorties, design hours : 1000 [hours]

operational wing loading : 286 [N/m^2]

wing stress (3 g) during operation : 213 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.29 ["]

max.angle of attack (stalling angle) : 13.17 ["]

angle of attack at max.speed : 3.37 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° :0.10 [ ]

lift coefficient at max. angle of attack : 1.12 [ ]

lift coefficient at max.speed : 0.36 [ ]

induced drag coefficient at max.speed : 0.0098 [ ]

drag coefficient at max.speed : 0.0791 [ ]

drag coefficient (zero lift) : 0.0693 [ ]

calculation : *8* (speeds

stalling speed at sea-level (OW): 73 [km/u]

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

min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 87 [km/hr] at 1500 [m] (power:48 [%])

min. power speed (max range) : 100 [km/hr] at 1500 [m] (power:54 [%])

max.rate of climb speed : 81.5 [km/hr] at sea-level

cruising speed : 117 [km/hr] op 1500 [m] (power:71 [%])

design speed prop : 124 [km/hr]

maximum speed : 130 [km/hr] op 100 [m] (power:99 [%])

climbing speed at sea-level (without bombload) : 230 [m/min]

calculation : *9* (regarding various performances)

take-off distance at sea-level : 190 [m]

lift/drag ratio : 6.92 [ ]

max. practical ceiling : 4100 [m] with flying weight :434 [kg]

practical ceiling (operational weight): 3700 [m] with flying weight :466 [kg]

practical ceiling fully loaded (mtow- 1 hour fuel) : 3425 [m] with flying weight :488 [kg]

published ceiling (3000 [m]

climb to 1500m (without bombload) : 7.54 [min]

climb to 3000m (without bombload) : 20.65 [min]

max.dive speed : 281.5 [km/hr] at 2425 [m] height

load factor at max.angle turn 1.78 ["g"]

turn radius at 500m: 54 [m]

time needed for 360* turn 12.2 [seconds] at 500m

calculation *10* (action radius & endurance)

operational endurance : 3.11 [hours] with 1 crew and 20 [kg] useful load and 98.5 [%] fuel

published endurance : 2.78 [hours] with 1 crew and possible useful (bomb) load : 27 [kg] and 88.1 [%] fuel

action radius : 182 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload

max range theoretically with additional fuel tanks for total 119 [litre] fuel : 472 [km]

useful load with action-radius 250km : 0 [kg]

production (500 km) : 0 [tonkm/hour]

I-°=/

Literature :

Fokkers uit WOI page 20

Fokker, bouwer aan de wereldluchtvaart page 24,25,26

Warplanes page 32,084

They fought for the sky page 9

last check python :

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.

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