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Caudron G.II
role : advanced trainer
first flight : operational : June 1912
country : France
design :
production : unknown
general information :
Used for advanced training at Chartres before and at the start of WWI. Not suited for use at the front but the good flying qualities and sturdy construction made it a good training aircraft. It 4-wheel landing gear saved many poor landings. It was a single-seater. Many French pilots made there first solo flight on this type.
users : France
crew : 1
armament : no fixed armament
engine : 1 Gnome 7A Monosoupape air-cooled 7 -cylinder Monosoupape rotary engine 80 [hp](58.8 KW)
dimensions :
wingspan : 12.1 [m], length : 7.25 [m], height : 2.6[m]
wing area : 28.0 [m^2]
weights :
max.take-off weight : 700 [kg]
empty weight operational : 400 [kg] bombload : 0 [kg]
performance :
maximum speed : 106 [km/hr] at sea-level
service ceiling : unknown
endurance : 3.5 [hours]
estimated action radius : 167 [km]
description :
2½-bay sesquiplane 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 tailbooms
engine, fuel and bombload in or attached to fuselage, landing gear attached to the wing
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.62 [ ]
estimated diameter airscrew 2.68 [m]
angle of attack prop : 13.12 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.47 [m]
blade-tip speed at Vmax and max revs. : 171 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.54 [m]
calculated wing chord (rounded tips): 1.76 [m]
wing aspect ratio : 7.84 []
estimated gap : 1.59 [m]
gap/chord : 1.03 [ ]
seize (span*length*height) : 228 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.5 [kg/hr]
fuel consumption(cruise speed) : 19.3 [kg/hr] (26.3 [litre/hr]) at 79 [%] power
distance flown for 1 kg fuel : 4.95 [km/kg]
estimated total fuel capacity : 104 [litre] (77 [kg])
calculation : *3* (weight)
weight engine(s) dry : 109.4 [kg] = 1.86 [kg/KW]
weight 32 litre oil tank : 2.7 [kg]
oil tank filled with 0.4 litre oil : 0.4 [kg]
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) : 1.7 [kg]
weight cowling 2.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 13.5 [kg]
total weight propulsion system : 128 [kg](18.3 [%])
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weight tail boom : 19 [kg]
fuselage skeleton (wood gauge : 5.50 [cm]): 56 [kg]
bracing : 3.0 [kg]
fuselage covering ( 6.5 [m2] doped linen fabric) : 2.1 [kg]
weight controls + indicators: 6.1 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 93 [litre] main fuel tank empty : 7.5 [kg]
weight engine mounts & firewalls : 3 [kg]
total weight fuselage : 86 [kg](12.3 [%])
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weight wing covering (doped linen fabric) : 18 [kg]
total weight ribs (37 ribs) : 42 [kg]
load on front upper spar (clmax) per running metre : 471.2 [N]
load on rear upper spar (vmax) per running metre : 151.5 [N]
total weight 8 spars : 32 [kg]
weight wings : 92 [kg]
weight wing/square meter : 3.27 [kg]
weight 12 interplane struts & cabane : 23.1 [kg]
weight cables (65 [m]) : 3.8 [kg] (= 58 [gram] per metre)
diameter cable : 3.1 [mm]
weight fin & rudder (1.7 [m2]) : 5.8 [kg]
weight stabilizer & elevator (3.2 [m2]): 10.5 [kg]
total weight wing surfaces & bracing : 135 [kg] (19.3 [%])
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weight armament : 0 [kg]
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wheel pressure : 175.0 [kg]
weight 4 wheels (610 [mm] by 72 [mm]) : 22.0 [kg]
weight tailskid : 1.9 [kg]
weight undercarriage with axle 15.9 [kg]
total weight landing gear : 39.8 [kg] (5.7 [%]
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calculated empty weight : 388 [kg](55.5 [%])
weight oil for 4.2 hours flying : 27.2 [kg]
*******************************************************************
calculated operational weight empty : 416 [kg] (59.4 [%])
published operational weight empty : 400 [kg] (57.1 [%])
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weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 39 [kg]
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operational weight : 535 [kg](76.4 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 585 [kg]
fuel reserve : 38 [kg] enough for 1.97 [hours] flying
possible additional useful load : 77 [kg]
operational weight fully loaded : 700 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 700 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 9.09 [kg/kW]
total power : 58.8 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.9 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] loadfactor : 2.3 [g]
design flight time : 2.80 [hours]
design cycles : 393 sorties, design hours : 1100 [hours]
operational wing loading : 187 [N/m^2]
wing stress (3 g) during operation : 172 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.17 ["]
max.angle of attack (stalling angle) : 12.30 ["]
angle of attack at max.speed : 3.01 ["]
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 : 0.36 [ ]
induced drag coefficient at max.speed : 0.0069 [ ]
drag coefficient at max.speed : 0.0824 [ ]
drag coefficient (zero lift) : 0.0756 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 59 [km/u]
landing speed at sea-level (OW without bombload): 71 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 68 [km/hr] at 1000 [m] (power:40 [%])
min. power speed (max range) : 68 [km/hr] at 1000 [m] (power:40 [%])
max.rate of climb speed : 64.0 [km/hr] at sea-level
cruising speed : 95 [km/hr] op 1000 [m] (power:70 [%])
design speed prop : 101 [km/hr]
maximum speed : 106 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 221 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 135 [m]
lift/drag ratio : 7.82 [ ]
max. practical ceiling : 4900 [m] with flying weight :506 [kg]
practical ceiling (operational weight): 4600 [m] with flying weight :535 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 3125 [m] with flying weight :681 [kg]
published ceiling (0 [m]
climb to 1500m (without bombload) : 7.60 [min]
climb to 3000m (without bombload) : 18.87 [min]
max.dive speed : 215.9 [km/hr] at 2125 [m] height
load factor at max.angle turn 2.06 ["g"]
turn radius at 500m: 33 [m]
time needed for 360* turn 8.5 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 3.97 [hours] with 1 crew and 127 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 3.50 [hours] with 1 crew and possible useful (bomb) load : 136 [kg] and 88.1 [%] fuel
action radius : 454 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 278 [litre] fuel : 1008 [km]
useful load with action-radius 250km : 103 [kg]
production : 9.78 [tonkm/hour]
oil and fuel consumption per tonkm : 2.63 [kg]
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Literature :
They fought for the sky page 033
Historische vliegtuigen page112
Bombers 1914-19 page 165
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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(c) B van der Zalm 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.2(64-bit)