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Maurice Farman M.F.11 "Shorthorn"
role : light bomber
first flight : early 1914 operational : May 1914
country : France
design : Maurice Farman
production : 300+ MF.11 + MF.11bis at Billancourt
information: Derived from the M.F.7, the MF.11 differed in lacking
the forward-mounted elevator. Without the front elevator it was nicknamed “Shorthorn” by the British who operated the type indicated as S.11 with the RNAS and RFC. It was a useful aircraft and used in great numbers in the first stages of WO I for reconnaissance and bombing raids. The observer took soon for defense a hand-held machine-gun with him, however 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. S.11 aircraft of the RNAS were the first to conduct a night bomb-raid in WOI. This happened on 21 December 1914 when S.11s bombed artillery-positions near Oostende, dropping eighteen 16 lb. H.E.R.L bombs. In autumn 1915 the MF.11 began to be replaced at the Western Front but continued to be widely used as training aircraft.
Headed into the wind it tended to remain almost stationary and become an easy target for ground defenses
crew : 2
users : France (37 escadrilles), RFC (1,2,4,9,16
and 30 sq.at the western front), RNAS (90), Italy (24 sq.), Russia
armament : no fixed armament, hand-held machine-gun.
engine : 1 Renault air-cooled 8-cylinder V-engine 100 [hp](74 KW)
dimensions :
wingspan : 16.15 [m], length : 9.45 [m], height : 3.18[m]
wing area : 57.0 [m^2]
weights :
max.take-off weight : 928 [kg]
empty weight operational : 650 [kg] bombload : 130 [kg]
performance :
maximum speed : 106 [km/hr] at sea-level
service ceiling : 3800 [m]
endurance : 3.5 [hours]
estimated action radius : 167 [km]
description :
3˝-bay biplane with fixed underwing 4-wheel landing gear and tail strut
airscrew :
fixed pitch 2 -bladed pusher airscrew with max. efficiency :0.62 [ ]
diameter airscrew 2.89 [m]
airscrew revs : 750 [r.p.m.]
pitch at Max speed 2.36 [m]
blade-tip speed at Vmax and max revs. : 117 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.96 [m]
calculated wing chord (rounded tips): 2.16 [m]
wing aspect ratio : 8.24 []
gap : 1.90 [m]
gap/chord : 0.97 [ ]
seize (span*length*height) : 485 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 1.7 [kg/hr]
fuel consumption(cruise speed) : 25.0 [kg/hr] (34.1 [litre/hr]) at 54.0 [KW] power
estimated specific fuel consumption (cruise power) : 463 [gram/kwh]
estimated specific oil consumption (cruise power) : 23 [gram/kwh]
distance flown for 1 kg fuel : 3.82 [km/kg]
estimated total fuel capacity : 135 [litre] (99 [kg])
calculation : *3* (weight)
weight engine(s) dry : 258.2 [kg] = 3.51 [kg/KW]
weight reduction gear : 2.9 [kg]
weight 10 litre oil tank : 0.8 [kg]
oil tank filled with 0.6 litre oil : 0.5 [kg]
oil in engine 0 litre oil : 0.4 [kg]
fuel in engine 1 litre fuel : 0.4 [kg]
weight 14 litre gravity patrol tank(s) : 2.2 [kg]
weight cowling 2.9 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 16.9 [kg]
total weight propulsion system : 287 [kg](31.0 [%])
*************************************************************
weight tail boom : 20 [kg]
fuselage skeleton (wood gauge : 5.02 [cm]): 61 [kg]
bracing : 4.3 [kg]
fuselage covering (doped linen fabric) : 3.7 [kg]
weight controls + indicators: 7.2 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 9.1 [kg]
weight 121 [litre] main fuel tank empty : 9.4 [kg]
weight engine mount & firewall : 4 [kg]
total weight fuselage : 109 [kg](11.8 [%])
***************************************************************
weight wing covering (doped linen fabric) : 39 [kg]
total weight ribs (39 ribs) : 55 [kg]
load on front upper spar (clmax) per running metre : 391.5 [N]
load on rear upper spar (vmax) per running metre : 184.5 [N]
total weight 8 spars : 46 [kg]
weight wings : 140 [kg]
weight wing/square meter : 2.46 [kg]
load on front upper spar (clmax) per bay : 790.3 [N]
gap : 1.90 [m]
weight 16 struts : 36.4 [kg]
weight cables (105 [m]) : 8.8 [kg] (= 84 [gram] per metre)
diameter cable : 3.7 [mm]
weight fin & rudder (3.0 [m2]) : 7.9 [kg]
weight stabilizer & elevator (5.5 [m2]): 13.8 [kg]
total weight wing surfaces & bracing : 207 [kg] (22.3 [%])
*******************************************************************
weight armament : 0 [kg]
********************************************************************
total weight landing gear : 42.5 [kg] (4.6 [%])
weight 4 wheels (700 [mm] by 78 [mm]) : 19.8 [kg]
weight tailskid : 2.5 [kg]
weight undercarriage with axle 20.3 [kg]
*******************************************************************
********************************************************************
calculated empty weight : 646 [kg](69.7 [%])
weight oil for 4.2 hours flying : 7 [kg]
*******************************************************************
calculated operational weight empty : 654 [kg] (70.4 [%])
published operational weight empty : 650 [kg] (70.0 [%])
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weight crew : 180 [kg]
weight fuel for 2.0 hours flying : 50 [kg]
********************************************************************
operational weight : 883 [kg](95.2 [%])
bombload could not be carried with fuel for 2 hours flying time
fuel reserve : 45 [kg] enough for 1.78 [hours] flying
operational weight fully loaded : 928 [kg] with fuel tank filled for 95 [%]
published maximum take-off weight : 928 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
engine total stroke volume (displacement): 8.8 [litre]
mean engine pressure : 25.07 [kg/cm2]
compression ratio : 4.55 : 1
power loading (Take-off) : 12.62 [kg/kW]
total power : 73.6 [kW] at 1500 [r.p.m]
power / stroke volume : 8.4 [kW/litre]
calculation : *5* (loads)
manoeuvre load : 2.7 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g]
design flight time : 2.80 [hours]
design cycles : 286 sorties, design hours : 800 [hours]
wing loading (MTOW) : 160 [N/m^2]
wing stress (3 g) during operation : 195 [N/kg] at 3g emergency manoeuvre
Italian MF11,with a 100 hp FIAT A-10 liquid/cooled in-line engine
calculation : *6* (angles of attack)
angle of attack zero lift : -1.16 ["]
max.angle of attack (stalling angle) : 13.55 ["]
angle of attack at max.speed : 2.19 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.27 [ ]
lift coefficient at max.speed : 0.29 [ ]
induced drag coefficient at max.speed : 0.0043 [ ]
drag coefficient at max.speed : 0.0513 [ ]
drag coefficient (zero lift) : 0.0470 [ ]
calculation : *8* (speeds
stalling speed at sea-level (MTOW): 52 [km/u]
landing speed at sea-level (OW without bombload): 60 [km/hr]
min.power speed (max endurance) : 63 [km/hr] op 1786 [m](P:27.9 [KW])
min.drag speed (max range) : 83 [km/hr] op 1786 [m] (P:37.6 [KW])
max.rate of climb speed : 63.9 [km/hr] at sea-level
cruising speed : 95 [km/hr] op 1786 [m](P:49.2 [KW])
design speed prop : 101 [km/hr]
maximum speed : 106 [km/hr] op 100 [m] (P:73 [KW])
climbing speed at sea-level (without bombload) : 169 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 77 [m]
lift/drag ratio : 10.16 [ ]
practical ceiling : 5450 [m] with flying weight :883 [kg]
practical ceiling : 5100 [m] with 130 [ kg] bombload :928 [kg]
climb to 1500m (without bombload) : 10.31 [min]
climb to 3000m (without bombload) : 24.88 [min]
published ceiling (3800 [m]) vmin : 60.9 [km/u] vmax : 99.1 [km/u]
max.dive speed : 329.4 [km/hr] at 4100 [m] height
load factor at max.angle turn 2.07 ["g"]
turn radius at 500m: 25 [m]
time needed for 360* turn 7.5 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.98 [hours] with 2 crew and 20 [kg] useful load and 75.0 [%] fuel
published endurance : 3.50 [hours] with possible useful (bomb) load : 7 [kg]
action radius : 142 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 252 [litre] fuel : 704 [km]
useful load with action-radius 250km : 54 [kg]
production : 5.11 [tonkm/hour]
oil and fuel consumption per tonkm : 5.23 [kg]
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IMPORTANCE : 4
literature :
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Jane’s fighter aircraft WW I
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(c) B van der Zalm 01 April 2018 python 3.4.1
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