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Maurice Farman M.F.11bis
role : two-seat armed reconnaissance and artillery observation
first flight : end 1914 operational : January 1915
country : France
design :
production : 100+ aircraft
general information :
In the early M.F.11 the observer took soon for defense a hand-held
machine-gun with him, but sitting behind the pilot his field of fire was limited. This led to the M.F.11bis in which they changed places. The observer in the front now had a clear field for his flexible mounted machine-gun. This type entered service in the first months of 1915. There are no records known an enemy airplane was brought down by a MF11bis.
users : France
crew : 2
armament : 1 movable 8.00 [mm] (0.315 in) Hotchkiss M1909 machine-gun for the observer
engine : 1 Renault V12 air-cooled 12 -cylinder V-engine 130 [hp](95.6 KW)
Cne Maurice Happe, to the right, commandant l'escadrille MF 29
posing for a MF11bis (with Canton-Unne engine ??)
dimensions :
wingspan : 15.78 [m], length : 9.3 [m], height : 3.15[m]
wing area : 57.0 [m^2]
weights :
max.take-off weight : 960 [kg]
empty weight operational (estimation): 670.0 [kg] bombload : 130 [kg]
performance :
maximum speed : 116 [km/hr] at sea-level
climbing speed : 126 [m/min]
service ceiling : 3800 [m]
endurance : 3.0 [hours]
estimated action radius : 157 [km]
description :
3-bay biplane with fixed underwing 4 -wheel landing gear and tail strut
upper wingtips supported by slanted flying wires
two spar upper and lower wing
tail supported by two open tail booms
engine, fuel and bombload in or attached to fuselage, landing gear attached to the wing
airscrew :
fixed pitch 2 -bladed pusher airscrew with max. efficiency :0.63 [ ]
estimated diameter airscrew 2.64 [m]
angle of attack prop : 22.51 [ ]
reduction : 0.50 [ ]
airscrew revs : 750 [r.p.m.]
pitch at Max speed 2.58 [m]
blade-tip speed at Vmax and max revs. : 109 [m/s]
calculation : *1* (dimensions)
mean wing chord : 2.01 [m]
calculated wing chord (rounded tips): 2.22 [m]
wing aspect ratio : 7.86 []
gap : 1.90 [m]
gap/chord : 0.95 [ ]
seize (span*length*height) : 462 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.0 [kg/hr]
fuel consumption(cruise speed) : 27.6 [kg/hr] (37.6 [litre/hr]) at 66 [%] power
distance flown for 1 kg fuel : 3.79 [km/kg]
estimated total fuel capacity : 128 [litre] (94 [kg])
calculation : *3* (weight)
weight engine(s) dry : 258.2 [kg] = 2.70 [kg/KW]
weight reduction gear : 3.8 [kg]
weight 10 litre oil tank : 0.9 [kg]
oil tank filled with 0.7 litre oil : 0.6 [kg]
oil in engine 1 litre oil : 0.5 [kg]
fuel in engine 1 litre fuel : 0.5 [kg]
weight 16 litre gravity patrol tank(s) : 2.4 [kg]
weight cowling 3.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 293 [kg](30.5 [%])
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weight tail boom : 24 [kg]
fuselage skeleton (wood gauge : 5.54 [cm]): 73 [kg]
bracing : 5.0 [kg]
fuselage covering ( 10.6 [m2] doped linen fabric) : 3.4 [kg]
weight controls + indicators: 7.1 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 9.1 [kg]
weight 112 [litre] main fuel tank empty : 9.0 [kg]
weight engine mounts & firewalls : 5 [kg]
total weight fuselage : 123 [kg](12.8 [%])
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France MF 11 of MF 1 based at Tronquoy (Somme), march 1916
weight wing covering (doped linen fabric) : 36 [kg]
total weight ribs (39 ribs) : 57 [kg]
load on front upper spar (clmax) per running metre : 343.3 [N]
load on rear upper spar (vmax) per running metre : 137.1 [N]
total weight 8 spars : 40 [kg]
weight wings : 133 [kg]
weight wing/square meter : 2.34 [kg]
weight 12 interplane struts & cabane : 29.5 [kg]
weight cables (95 [m]) : 6.8 [kg] (= 72 [gram] per metre)
diameter cable : 3.4 [mm]
weight fin & rudder (2.9 [m2]) : 7.2 [kg]
weight stabilizer & elevator (5.5 [m2]): 13.2 [kg]
total weight wing surfaces & bracing : 190 [kg] (19.8 [%])
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weight machine-gun(s) : 12.0 [kg]
weight pivot mounting mg :5.0 [kg]
weight armament : 17 [kg]
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good soft ground capabilities
wheel pressure : 240.0 [kg]
weight 4 wheels (710 [mm] by 84 [mm]) : 28.2 [kg]
weight tailskid : 1.9 [kg]
weight undercarriage with axle 14.0 [kg]
total weight landing gear : 44.2 [kg] (4.6 [%]
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calculated empty weight : 666 [kg](69.4 [%])
weight oil for 3.6 hours flying : 7.2 [kg]
weight 8 drums empty : 0.9 [kg]
weight ammunition (192 rounds) : 7.7 [kg]
*******************************************************************
The MF11 bis did not have slanted struts to the wingtips
calculated operational weight empty : 681 [kg] (71.0 [%])
estimated operational weight empty : 670 [kg] (69.8 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 55 [kg]
********************************************************************
operational weight : 898 [kg](93.6 [%])
bombload could not be carried with fuel for 2 hours flying time
weight camera : 20 [kg]
operational weight photo mission : 918 [kg]
fuel reserve : 39 [kg] enough for 1.41 [hours] flying
possible additional useful load : 3 [kg]
operational weight fully loaded : 960 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 960 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 9.39 [kg/kW]
total power : 95.6 [kW] at 1500 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.7 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 1.9 [g]
design flight time : 2.40 [hours]
design cycles : 275 sorties, design hours : 660 [hours]
operational wing loading : 158 [N/m^2]
wing stress (3 g) during operation : 203 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.17 ["]
max.angle of attack (stalling angle) : 12.29 ["]
angle of attack at max.speed : 1.70 ["]
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 : 0.25 [ ]
induced drag coefficient at max.speed : 0.0032 [ ]
drag coefficient at max.speed : 0.0510 [ ]
drag coefficient (zero lift) : 0.0478 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 53 [km/u]
landing speed at sea-level (OW without bombload): 64 [km/hr]
min.drag speed (max endurance) : 65 [km/hr] at 1900 [m](power :32 [%])
min. power speed (max range) : 75 [km/hr] at 1900 [m] (power:36 [%])
max.rate of climb speed : 68.5 [km/hr] at sea-level
cruising speed : 104 [km/hr] op 1900 [m] (power:65 [%])
design speed prop : 110 [km/hr]
maximum speed : 116 [km/hr] op 100 [m] (power:98 [%])
climbing speed at sea-level (without bombload) : 230 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 95 [m]
lift/drag ratio : 9.85 [ ]
max. practical ceiling : 5075 [m] with flying weight :768 [kg]
practical ceiling (operational weight): 4475 [m] with flying weight :898 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 4300 [m] with flying weight :932 [kg]
published ceiling (3800 [m]
climb to 1500m (without bombload) : 7.39 [min]
climb to 3000m (without bombload) : 18.78 [min]
max.dive speed : 288.3 [km/hr] at 3300 [m] height
load factor at max.angle turn 2.39 ["g"]
turn radius at 500m: 26 [m]
time needed for 360* turn 7.0 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 3.51 [hours] with 2 crew and 20 [kg] useful load and 103.2 [%] fuel
published endurance : 3.00 [hours] with 2 crew and possible useful (bomb) load : 34 [kg] and 88.1 [%] fuel
action radius : 183 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 297 [litre] fuel : 824 [km]
useful load with action-radius 250km : 86 [kg]
production : 8.93 [tonkm/hour]
oil and fuel consumption per tonkm : 3.31 [kg]
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Literature :
Fighters 1914-19 page 97
Wikipedia
They fought for the sky page 33
Praktisch handbook vliegtuigen deel 1 page 132
Warplanes WOI page 42
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 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4
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