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weight and performance calculations for the Farman F.60 Goliath
Farman F.60 Goliath
role : passenger aircraft
importance : ****
first flight : operational : February 1919
country : France
design :
production : 60 aircraft
general information :
Designed in WWI as heavy bomber but after the armistice it was altered into a passenger aircraft. On 1 April 1919 a F.60 reached a height of 6300m with 4 passengers in 1 hour 5 minutes. 2 days later it flew to 6200m with 14 passengers in the same time and on 05 May 1919 it reached 5100m with 25 passengers in 1 hour 15 minutes ! In August 1919 a Goliath flew in 18 hours 23 minutes from Paris to Casablanca with a crew of 8, a distance of ca. 2050 km (average speed 111.5 km/hr). The first regular passenger service was made on 20 March 1920, it was between Paris and London. Later it also flew to Amsterdam, Brussel and Berlin. It was used by all the major European airlines. About 1930 one Goliath had made 2962 flying hours. And in 1933 one had accumulated 3843 flying hours !
users : Compagnie des Grands Express Aeriens, Compagnie des Messageries Aeriennes, Societe Generale de Transports Aeriens (Lignes Farman), Air Union, Compagnie Aerienne Francaise, Sabena, CSA, Lares
crew : 2 passengers : 12
engine : 2 Salmson Canton-Unne C.M. liquid-cooled 9 -cylinder radial engine 260 [hp](193.9 KW)
dimensions :
wingspan : 26.46 [m], length : 14.33 [m], height : 4.9[m]
wing area : 164.9 [m^2]
weights :
max.take-off weight : 4770 [kg]
empty weight operational (estimation): 2850.0 [kg] useful load : 1300 [kg]
performance :
maximum speed :133 [km/u] op 2000 [m]
cruise speed :120 [km/u] op 2000 [m]
service ceiling : 5100 [m]
range : 400 [km]
description :
3-bay biplane with fixed underwing 4 -wheel landing gear and tail strut
two spar upper and lower wing
engines,landing gear and fuel attached to the wings, useful load inside the fuselage
airscrew :
two fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.64 [ ]
diameter airscrew 2.34 [m]
angle of attack prop : 14.58 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1550 [r.p.m.]
pitch at Max speed 1.43 [m]
blade-tip speed at Vmax and max revs. : 193 [m/s]
calculation : *1* (dimensions)
wing chord : 3.12 [m]
mean wing chord : 3.12 [m]
calculated wing chord (rounded leading edge tips): 3.17 [m]
wing aspect ratio : 8.49 []
gap : 3.00 [m]
gap/chord : 0.96 [ ]
seize (span*length*height) : 1858 [m^3]
O-BLAN in flight, it crashed on 26 August 1921 in the channel, near Calais after an inflight explosion
calculation : *2* (fuel consumption)
oil consumption : 13.6 [kg/hr]
fuel consumption(cruise speed) : 88.8 [kg/hr] (121.1 [litre/hr]) at 66 [%] power
distance flown for 1 kg fuel : 1.35 [km/kg] at 2550 [m] cruise height, sfc : 345.1 [kg/kwh]
estimated total fuel capacity : 458.16 [litre] (335.83 [kg])
calculation : *3* (weight)
weight engine(s) dry : 698.0 [kg] = 1.80 [kg/KW]
weight 70.2 litre oil tank : 5.96 [kg]
oil tank filled with 2.9 litre oil : 2.6 [kg]
oil in engine 21.6 litre oil : 19.4 [kg]
fuel in engine 2.6 litre fuel : 1.94 [kg]
weight 51.5 litre gravity patrol tank(s) : 7.7 [kg]
weight radiator : 55.6 [kg]
weight exhaust pipes & fuel lines 27.2 [kg]
weight self-starter : 4.8 [kg]
weight cowling 7.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 23.7 [kg]
total weight propulsion system : 849 [kg](17.8 [%])
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fuselage skeleton (wood gauge : 11.60 [cm]): 494 [kg]
fuselage width : 1.31 [m]
Chord 10 ft 3 in = 3.12m area of main planes : 1775 sq.ft = 164.9 m2 gap : 9 ft 10 in = 3.00m
passenger seating pitch : 87 [cm]
passenger cabin width : 1.19 [m] cabin length : 5.22 [m]
normal weight luggage & freight 376 [kg] luggage/freight
suitable for light volumetric freight, not to much load near the tail for COG
bracing : 53.7 [kg]
fuselage covering ( 38.8 [m2] doped linen fabric) : 12.4 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 8.3 [kg]
weight seats : 42.0 [kg]
weight interior + equipment + fuel lines: 63 [kg]
total weight fuselage : 677 [kg](14.2 [%])
***************************************************************
weight wing covering (doped linen fabric) : 129 [kg]
Seating layout 6 rows (1+1)
total weight ribs (125 ribs) : 284 [kg]
weight engine mounts : 19 [kg]
weight two 203 [litre] main fuel tanks empty : 32.5 [kg]
load on front upper spar (clmax) per running metre : 810.0 [N]
load on rear upper spar (vmax) per running metre : 389.4 [N]
total weight 8 spars : 228 [kg]
weight wings : 641 [kg]
weight wing/square meter : 3.89 [kg]
weight 12 interplane struts & cabane : 231.4 [kg]
weight cables (174 [m]) : 62.4 [kg] (= 359 [gram] per metre)
diameter cable : 7.7 [mm]
weight fin & rudder (8.1 [m2]) : 32.8 [kg]
weight stabilizer & elevator (18.6 [m2]): 73.3 [kg]
total weight wing surfaces & bracing : 1093 [kg] (22.9 [%])
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wheel pressure : 1192.5 [kg]
weight 4 wheels (950 [mm] by 146 [mm]) : 110.0 [kg]
weight tailskid : 8.5 [kg]
weight undercarriage with axle 102.1 [kg]
total weight landing gear : 220.6 [kg] (4.6 [%]
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calculated empty weight : 2839 [kg](59.5 [%])
weight oil for 4.0 hours flying : 54.3 [kg]
weight cooling fluids : 83.8 [kg]
calculated operational weight empty : 2977 [kg] (62.4 [%])
estimated operational weight empty : 2850 [kg] (59.7 [%])
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weight crew : 162 [kg]
weight fuel for 1.0 hours flying : 89 [kg]
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operational weight : 3227 [kg](67.7 [%])
fuel reserve : 247.1 [kg] enough for 2.78 [hours] flying
possible additional useful load : 1296 [kg]
operational weight fully loaded : 4770 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 4770 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 12.30 [kg/kW]
power loading (operational without useful load) : 8.32 [kg/kW]
total power : 387.8 [kW] at 1550 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.9 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 2.67 [hours]
design cycles : 281 sorties, design hours : 750 [hours]
operational wing loading : 192 [N/m^2]
wing stress (3 g) during operation : 148 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.15 ["]
max. angle of attack (stalling angle) : 12.03 ["]
angle of attack at max. speed : 2.05 ["]
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 : 0.28 [ ]
induced drag coefficient at max. speed : 0.0052 [ ]
drag coefficient at max. speed : 0.0466 [ ]
drag coefficient (zero lift) : 0.0414 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 60 [km/u]
stalling speed at sea-level (MTOW): 72 [km/u]
landing speed at sea-level: 70 [km/hr]
min. drag speed (max endurance) : 81 [km/hr] at 2550 [m](power :35 [%])
min. power speed (max range) : 91 [km/hr] at 2550 [m] (power:37 [%])
max. rate of climb speed : 81.2 [km/hr] at sea-level
cruising speed : 120 [km/hr] op 2550 [m] (power:59 [%])
design speed prop : 127 [km/hr]
maximum speed : 133 [km/hr] op 2000 [m] (power:79 [%])
climbing speed at sea-level : 265 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 86.9 [km/u]
static prop wash : 103 [km/u]
take-off distance at sea-level : 242 [m]
lift/drag ratio : 9.52 [ ]
time to 2000m : 9.43 [min]
climb to 3000m : 15.54 [min]
published ceiling (5100 [m]
practical ceiling (operational weight) : 7003 [m] with flying weight :3227 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 4338 [m] with flying weight :4726 [kg]
max. dive speed : 355.5 [km/hr] at 3338 [m] height
calculation *10* (action radius & endurance)
published range : 400 [km] with 2 crew and 1335.5 [kg] useful load and 88.1 [%] fuel
range : 448 [km] with 2 crew and 1300.0 [kg] useful load and 98.7 [%] fuel
max range theoretically with additional fuel tanks for total 2336.2 [litre] fuel : 2315.0 [km]
useful load with range 500km : 1343 [kg]
production : 161.11 [tonkm/hour]
oil and fuel consumption per tonkm : 0.64 [kg]
_
I_°°>/
°
The remains of F-GEAD after a mid-air collision
Accidents :
10 fatal accidents with total 27 fatalities.
*26 August 1921 Goliath O-BLAN c/n 7248/17 of SNETA (Belgium) operating a mail flight from London – Croydon airport to Brussel-Haren airport. Both crew died.
*On 7 April 1922 Goliath F-GEAD of Grands Express Aeriens made a Mid Air Crash above Poix/ Grandvillers, with a De Havilland DH18A G-EAWO which was on a mail flight from Croydon to Le Bourget. The 2 crew and 3 passenger aboard the Goliath died. The 2 crew of the DH18A also died in the crash. first MAC of two civil airplanes.
*14 May 1923 Goliath F-AEBY in flight failure : los of wing, crashed near Monsures, Somme, France, 2 crew and 4 passengers died
*27 August 1923 Goliath F-AECB of Air Union crashed at East Malling, Kent due to engine failure and passenger misunderstanding to move to the aft affecting the Centre of Gravity. 1 dead
Crashed F-AECB
*16 October 1925 Goliath F-HMFU of Air Union crashed near Wadhurst, East-Sussex, 3 dead
F-HMFU in better times
*05 May 1927 F.61 Goliath F-ADFN of the SGTA crashed in the Atlantic Ocean on a cargo flight from Senegal to Brazil, 2 crew died. Pilot : Jacques de Serre
*11 March 1928 F.60 Goliath F-AEFC of Air Union crashed 14.5 km South East of Folkestone in the sea. 2 crew died
*23 May 1928 F.63bis Goliath F-AEIE , Germany of Societe Generale des Transports Aeriens (SGTA), crashed on TO Butzweilerhof airport, near Koln, Germany and consumed by fire, 2 crew and 1 passenger killed.
F-AEIE, An F.63bis powered by 365hp Armstrong Siddeley III Jaguar engines or 380hp Gnome Rhone 9Aa Jupiter engines
*10 February 1930 F.63bis Goliath F-FHMY Marden , UK of Air Union, Kent, flight Le Bourget to Croydon, crashed on landing. 2 dead, 4 wounded
*09 July 1930 F.63 bis Goliath F-ADFQ of Societe Generale des Transports Aeriens (SGTA), elevator control cable failed shortly after TO Schiphol airport, Amsterdam, crashed near Aalsmeer. mail flight Schiphol to Le Bourget. 1 crew member died in the crash.
Wreckage of F-ADFQ near Aalsmeer, the Netherlands
Literature :
Praktisch handbook vliegtuigen deel 2 page 20,21
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/
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(c) B van der Zalm 01 January 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4