Maurice Farman M.F.7 Longhorn | aircraft investigation

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Maurice Farman M.F.7 "Longhorn"

role : two-seat unarmed reconnaissance

first flight : spring 1912 operational : August 1913

country : France

design :

production : unknown, at Billancourt

general information :

The “Longhorn” also indicated as Type 1913 and the M.F.11 “Shorthorn” were successful and popular aircraft used from the beginning of WWI trough 1915 for reconnaissance by the French, Belgian, British and Italian air forces. The M.F7 was succeeded by the M.F.11 in 1915. But they continued as trainer for a long time.

The “Longhorn” has a extended landing skid bended upwards to support the Canard wing.

The British RFC used the M.F.7 (indicated as S.7) with 2,4 and 6 squadrons. Those aircraft were built in the UK.

The Farman aircraft factory at Billancourt was the only factory at the start of WWI capable of mass production of aircraft.

During the French military manoeuvres in 1911 experiments took place with making aerial photographs using Farman aircraft. At the beginning of WWI, the “Longhorn” was used in Chartres for advanced training. It did not have dual control and the pupil sat behind the pilot. If the instructor was convinced the pupil could fly, he allowed him to take the control reaching over his shoulders. After 2 hours flying like this the pupil could make his first solo flight. The front elevator (canard) gave unexpected flying behaviour and led to crashes for the novices. The airframe was not to strong, but this had the advantage that in case of a crash the frame absorbed much of the impact saving the crew.

users : France, Belgium, RFC, Italy

crew : 2

armament : no fixed armament

engine : 1 Renault V8 air-cooled 8 -cylinder V-engine 70 [hp](51.5 KW)

dimensions :

wingspan : 15.52 [m], length : 11.35 [m], height : 3.45[m]

wing area : 48.31 [m^2]

weights :

max.take-off weight : 855 [kg]

empty weight operational : 550 [kg] bombload : 0 [kg]

performance :

maximum speed : 95 [km/hr] at sea-level

service ceiling : 4000 [m]

endurance : 3.5 [hours]

estimated action radius : 150 [km]

description :

3½-bay biplane with fixed underwing 4 -wheel landing gear and tail strut

upper wingtips supported by slanted struts

two spar upper and lower wing

tail supported by two open tail booms

canard wing

engine, fuel and bombload in or attached to fuselage, landing gear attached to the wing

$C:\Users\Eigenaar\Pictures\MF7 Longhorn drawing.png$

airscrew :

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

estimated diameter airscrew 2.73 [m]

angle of attack prop : 17.95 [ ]

reduction : 0.50 [ ]

airscrew revs : 760 [r.p.m.]

pitch at Max speed 2.08 [m]

blade-tip speed at Vmax and max revs. : 112 [m/s]

calculation : *1* (dimensions)

mean wing chord : 1.73 [m]

calculated wing chord (rounded tips): 1.90 [m]

wing aspect ratio : 8.97 []

estimated gap : 2.05 [m]

gap/chord : 1.19 [ ]

seize (span*length*height) : 608 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 1.2 [kg/hr]

fuel consumption(cruise speed) : 18.6 [kg/hr] (25.4 [litre/hr]) at 68 [%] power

distance flown for 1 kg fuel : 4.59 [km/kg]

estimated total fuel capacity : 101 [litre] (74 [kg])

calculation : *3* (weight)

weight engine(s) dry : 180.0 [kg] = 3.50 [kg/KW]

weight reduction gear : 2.1 [kg]

weight 7 litre oil tank : 0.6 [kg]

oil tank filled with 0.4 litre oil : 0.3 [kg]

$C:\Users\Eigenaar\Pictures\MF7 longhorn foto.jpg$

oil in engine 0 litre oil : 0.3 [kg]

fuel in engine 0 litre fuel : 0.3 [kg]

weight 11 litre gravity patrol tank(s) : 1.6 [kg]

weight cowling 2.1 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 11.8 [kg]

total weight propulsion system : 201 [kg](23.5 [%])

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weight tail boom : 24 [kg]

fuselage skeleton (wood gauge : 5.03 [cm]): 73 [kg]

bracing : 5.1 [kg]

fuselage covering ( 15.8 [m2] doped linen fabric) : 5.1 [kg]

weight controls + indicators: 7.6 [kg]

weight seats : 6.0 [kg]

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

weight 90 [litre] main fuel tank empty : 7.2 [kg]

weight engine mounts & firewalls : 3 [kg]

total weight fuselage : 112 [kg](13.1 [%])

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

weight wing covering (doped linen fabric) : 31 [kg]

total weight ribs (40 ribs) : 51 [kg]

load on front upper spar (clmax) per running metre : 344.3 [N]

load on rear upper spar (vmax) per running metre : 134.0 [N]

total weight 8 spars : 38 [kg]

weight wings : 120 [kg]

weight wing/square meter : 2.49 [kg]

weight 16 interplane struts & cabane : 48.6 [kg]

weight cables (107 [m]) : 7.4 [kg] (= 70 [gram] per metre)

diameter cable : 3.4 [mm]

weight fin & rudder (2.8 [m2]) : 7.4 [kg]

weight stabilizer & elevator (4.6 [m2]): 11.9 [kg]

total weight wing surfaces & bracing : 195 [kg] (22.9 [%])

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

weight armament : 0 [kg]

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

wheel pressure : 213.8 [kg]

weight 4 wheels (620 [mm] by 73 [mm]) : 21.4 [kg]

weight tailskid : 1.7 [kg]

weight undercarriage with axle 15.9 [kg]

total weight landing gear : 39.1 [kg] (4.6 [%]

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calculated empty weight : 547 [kg](64.0 [%])

weight oil for 4.2 hours flying : 5.0 [kg]

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

calculated operational weight empty : 552 [kg] (64.6 [%])

published operational weight empty : 550 [kg] (64.3 [%])

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" "

weight crew : 162 [kg]

weight fuel for 2.0 hours flying : 37 [kg]

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

operational weight : 751 [kg](87.9 [%])

estimated bomb load : 50 [kg]

operational weight bombing mission : 801 [kg]

weight camera : 20 [kg]

operational weight photo mission : 771 [kg]

fuel reserve : 37 [kg] enough for 1.97 [hours] flying

possible additional useful load : 47 [kg]

operational weight fully loaded : 855 [kg] with fuel tank filled for 100 [%]

published maximum take-off weight : 855 [kg] (100.0 [%])

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calculation : * 4 * (engine power)

power loading (operational without bombload) : 14.59 [kg/kW]

total power : 51.5 [kW] at 1520 [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 : 1.9 [g]

design flight time : 2.80 [hours]

design cycles : 268 sorties, design hours : 750 [hours]

operational wing loading : 157 [N/m^2]

wing stress (3 g) during operation : 189 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.14 ["]

max.angle of attack (stalling angle) : 11.82 ["]

angle of attack at max.speed : 2.97 ["]

calculation : *7* (lift & drag ratios

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

lift coefficient at max. angle of attack : 1.14 [ ]

lift coefficient at max.speed : 0.36 [ ]

induced drag coefficient at max.speed : 0.0062 [ ]

drag coefficient at max.speed : 0.0584 [ ]

drag coefficient (zero lift) : 0.0523 [ ]

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) = minimum speed*1.1 at cruise height : 65 [km/hr] at 2000 [m] (power:45 [%])

min. power speed (max range) : 65 [km/hr] at 2000 [m] (power:45 [%])

max.rate of climb speed : 58.5 [km/hr] at sea-level

cruising speed : 86 [km/hr] op 2000 [m] (power:67 [%])

design speed prop : 90 [km/hr]

maximum speed : 95 [km/hr] op 100 [m] (power:99 [%])

climbing speed at sea-level (without bombload) : 131 [m/min]

calculation : *9* (regarding various performances)

take-off distance at sea-level : 175 [m]

lift/drag ratio : 10.06 [ ]

max. practical ceiling : 4575 [m] with flying weight :642 [kg]

practical ceiling (operational weight): 3675 [m] with flying weight :751 [kg]

practical ceiling fully loaded (mtow- 1 hour fuel) : 3025 [m] with flying weight :836 [kg]

published ceiling (4000 [m]

climb to 1500m (without bombload) : 13.04 [min]

climb to 3000m (without bombload) : 33.64 [min]

max.dive speed : 249.1 [km/hr] at 2025 [m] height

load factor at max.angle turn 1.85 ["g"]

turn radius at 500m: 29 [m]

time needed for 360* turn 8.6 [seconds] at 500m

calculation *10* (action radius & endurance)

operational endurance : 3.97 [hours] with 2 crew and 67 [kg] useful (bomb)load and 100.0 [%] fuel

published endurance : 3.50 [hours] with 2 crew and possible useful (bomb) load : 76

[kg] and 88.1 [%] fuel

action radius : 278 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload

max range theoretically with additional fuel tanks for total 303 [litre] fuel : 1020 [km]

useful load with action-radius 250km : 113 [kg]

production : 9.67 [tonkm/hour]

oil and fuel consumption per tonkm : 2.05 [kg]

°°_I>-/

Literature :

Jagdflugzeuge WOI blz.8

Praktisch Handboek vliegtuigen deel 1 blz.132,133

Historische vliegtuigen blz.38, 135

Fighters 1914-19 Munson blz.17

They fought fort he sky page 33

Jane’s FAWOI page 111

Flight 06 July 1912

www.flyingmachines.ru

warplanes page 9,20,21,22

Early aviation page 24f

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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