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weight and performance calculations for the Maurice Farman M.F.2
Maurice Farman M.F.2
role : experimental/research/flying trials
importance : ****
first flight : operational : October 1910
country : France
design : Maurice Farman
production : unknown
general information :
On 28 October 1910 at Etampes, Maurice Tabuteau set the record for distance in closed circuit at 466km.
465 km in 6 hr 1 min 35 sec = av. 77.2 km/hr 190 litre petrol used = 139.3 kg = 23.12
kg/hr, 3.34 km/kg 20 litre oil used.
On 30 December 1910 he improved his record by now flying 585 km at Buc.
585 km in 7 hr 48 min 31 sec = av. 74.9 km/hr, nog genoeg petrol voor 1 uur meer !
Then on 01 September 1911 M. Fourny flew 723 km at Buc and on 12 September 1912 Fourny again raised it to 1011 km, with a Maurice Farman biplane with 70 hp Renault engine, probably this was a M.F.7 type.
On 07 March 1911 Eugene Renaux made a remarkable flight by flying with a passenger, Albert Senoque, from St.Cloud, Paris to the Puy-de-Dome. After flying 366 km he landed at the top of the Puy at 1600m height after flying for 5 hrs 20m. 46s. A 15 min.stop was made on the way at Nevers, Peuplier aerodrome for replenishment. With this feat Renaux won the price Prix Michelin of 100.000 Frfr for flying with a passenger from Paris to the Puy-de-Dome within 6 hrs.
users : Maurice Tabuteau, M.Fourny, Eugene Renaux
crew : 1
engine : 1 Renault V8 60hp air-cooled 8 -cylinder V-engine 60 [hp](44.7 KW)
dimensions :
wingspan : 11.0 [m], length : 12.75 [m], height : 2.74[m]
wing area : 50.0 [m^2]
weights :
max.take-off weight : 700 [kg]
empty weight operational : 420 [kg] useful load : 0 [kg]
performance :
maximum speed :83 [km/hr] at sea-level
cruise speed :75 [km/u] op 50 [m]
service ceiling : 600 [m]
range : 725 [km]
estimated endurance : 9.71 [hours]
description :
3-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
tail supported by two open tail booms
canard wing
engines, landing gear, fuel and useful load in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed pusher airscrew with max. efficiency :0.61 [ ]
estimated diameter airscrew 2.75 [m]
angle of attack prop : 14.94 [ ]
fine pitch
reduction : 0.50 [ ]
airscrew revs : 800 [r.p.m.]
pitch at Max speed 1.73 [m]
blade-tip speed at Vmax and max revs. : 117 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.30 [m]
mean wing chord : 2.27 [m]
calculated wing chord (rounded tips): 2.61 [m]
wing aspect ratio : 4.84 []
estimated gap : 2.00 [m]
gap/chord : 0.88 [ ]
seize (span*length*height) : 384 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.0 [kg/hr]
fuel consumption(cruise speed) : 18.8 [kg/hr] (25.6 [litre/hr]) at 87 [%] power
distance flown for 1 kg fuel : 3.98 [km/kg] at 300 [m] cruise height, sfc : 482.5 [kg/kwh]
estimated total fuel capacity : 281.85 [litre] (206.59 [kg])
calculation : *3* (weight)
weight engine(s) dry : 170.0 [kg] = 3.80 [kg/KW]
weight reduction gear : 1.8 [kg]
weight 27.2 litre oil tank : 2.32 [kg]
oil tank filled with 0.3 litre oil : 0.3 [kg]
oil in engine 0.2 litre oil : 0.2 [kg]
fuel in engine 0.3 litre fuel : 0.22 [kg]
weight 10.9 litre gravity patrol tank(s) : 1.6 [kg]
weight cowling 1.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 11.5 [kg]
total weight propulsion system : 189 [kg](27.0 [%])
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weight tail boom : 10 [kg]
fuselage skeleton (wood gauge : 3.08 [cm]): 31 [kg]
bracing : 2.4 [kg]
fuselage covering ( 20.0 [m2] doped linen fabric) : 6.4 [kg]
weight instruments. : 1.1 [kg]
weight controls : 5.8 [kg]
weight seats : 3.0 [kg]
weight 271 [litre] main fuel tank empty : 21.7 [kg]
weight engine mount : 2.2 [kg]
total weight fuselage : 74 [kg](10.5 [%])
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weight wing covering (doped linen fabric) : 28 [kg]
total weight ribs (25 ribs) : 42 [kg]
load on front upper spar (clmax) per running metre : 167.1 [N]
load on rear upper spar (vmax) per running metre : 141.6 [N]
total weight 8 spars : 16 [kg]
weight wings : 86 [kg]
weight wing/square meter : 1.72 [kg]
weight 12 interplane struts & cabane : 20.1 [kg]
weight cables (97 [m]) : 1.7 [kg] (= 18 [gram] per metre)
diameter cable : 1.7 [mm]
area of canard wing : 2.4 [m2
weight canard wing :4.3 [kg]
weight fin & rudder (1.4 [m2]) : 2.6 [kg]
weight stabilizer & elevator (4.8 [m2]): 8.6 [kg]
total weight wing surfaces & bracing : 123 [kg] (17.6 [%])
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wheel pressure : 350.0 [kg]
weight 2 wheels (600 [mm] by 71 [mm]) : 15.8 [kg]
weight tailskid : 0.7 [kg]
weight undercarriage with axle 9.6 [kg]
total weight landing gear : 26.0 [kg] (3.7 [%]
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calculated empty weight : 412 [kg](58.9 [%])
weight oil for 11.6 hours flying : 23.4 [kg]
calculated operational weight empty : 436 [kg] (62.2 [%])
published operational weight empty : 420 [kg] (60.0 [%])
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weight crew : 81 [kg]
weight fuel for 1.0 hours flying : 19 [kg]
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operational weight : 535 [kg](76.5 [%])
fuel reserve : 164.6 [kg] enough for 8.77 [hours] flying
Henry Farman on his knees helps to install a 300 litre petrol tank in Tabuteau his M.F.2. Note the single wheel landing gear.
operational weight fully loaded : 700 [kg] with fuel tank filled for 89 [%]
published maximum take-off weight : 700 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 15.65 [kg/kW]
power loading (operational without useful load) : 11.97 [kg/kW]
total power : 44.7 [kW] at 1600 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.8 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 0.9 [g]
design flight time : 6.79 [hours]
design cycles : 19 sorties, design hours : 38 [hours]
operational wing loading : 105 [N/m^2]
wing stress (3 g) during operation : 183 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.36 ["]
max. angle of attack (stalling angle) : 13.46 ["]
angle of attack at max. speed : 3.06 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.09 [ ]
lift coefficient at max. speed : 0.32 [ ]
induced drag coefficient at max. speed : 0.0123 [ ]
drag coefficient at max. speed : 0.0724 [ ]
drag coefficient (zero lift) : 0.0601 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 45 [km/u]
stalling speed at sea-level (MTOW): 52 [km/u]
landing speed at sea-level: 53 [km/hr]
min. drag speed (max endurance) : 56 [km/hr] at 300 [m](power :55 [%])
min. power speed (max range) : 62 [km/hr] at 300 [m] (power:60 [%])
max. rate of climb speed : 54.1 [km/hr] at sea-level
cruising speed : 75 [km/hr] op 300 [m] (power:78 [%])
design speed prop : 79 [km/hr]
maximum speed : 83 [km/hr] op 50 [m] (power:99 [%])
climbing speed at sea-level : 130 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 56.9 [km/u]
emergency/TO power : 70 [hp] at 1781 [rpm]
static prop wash : 70 [km/u]
take-off distance at sea-level : 62 [m]
lift/drag ratio : 5.96 [ ]
time to 1000m : 9.39 [min]
time to 2000m : 23.41 [min]
practical ceiling (operational weight) : 3938 [m] with flying weight :535 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 1958 [m] with flying weight :691 [kg]
max. dive speed : 179.9 [km/hr] at 958 [m] height
turning speed at CLmax : 58.0 [km/u] at 50 [m] height
turn radius at 50m: 20 [m]
time needed for 360* turn 8.0 [seconds] at 50m
load factor at max. angle turn 1.64 ["g"]
calculation *10* (action radius & endurance)
estimated endurance : 9.71 [hours] with 1 crew and possible useful load : 1.3 [kg] and 88.1 [%] fuel
published range : 725 [km] with 1 crew and 1.3 [kg] useful load and 88.1 [%] fuel
max range theoretically with additional fuel tanks for total 250.1 [litre] fuel : 730.2 [km]
useful load with range 500km : 58 [kg]
production : 4.32 [tonkm/hour]
oil and fuel consumption per tonkm : 4.81 [kg]
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Literature :
https://www.hydroretro.net/etudegh/premiersfarman.pdf
Jane’s record breaking aircraft page 23
Historische vliegtuigen page 38,
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 07 October 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4