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weight and performance calculations for the Caudron G.6 armed reconnaissance biplane
Caudron G.6
role : two-seat armed reconnaissance and artillery observation
importance : ***
first flight : Spring 1916 operational : October 1916
country : France
design : Paul Deville
production : 512 aircraft
general information :
Combined normal fuselage with wing from G.IV. While the brothers Caudron had
collaborated closely in aircraft design up to this point, the similar G.5 and G.6 were the
work of Gaston Caudron, while the R.4 was by René Caudron
The Caudron G.6 came into Aviation Militaire service in the latter half of 1916, and it
served with at least 38 escadrilles until replaced with better planes in late 1917 and
early 1918.
More then 500 G.6 aircraft were built, with 302 on hand in August 1917.
users : France
crew : 2
armament : 2 movable 7.70 [mm] (0.303 in) Lewis machine-guns
engine : 2 Le Rhone 9jb air-cooled 9 -cylinder two-valve rotary engine 120 [hp](88.3 KW)
dimensions :
wingspan : 17.21 [m], length : 8.6 [m], height : 2.95[m]
wing area : 39.7 [m^2]
weights :
max.take-off weight : 1435 [kg]
empty weight operational : 940 [kg] bombload : 100 [kg]
performance :
maximum speed : 152 [km/hr] at sea-level
climbing speed : 264 [m/min]
service ceiling : 4725 [m]
endurance : 2.5 [hours]
estimated action radius : 171 [km]
description :
3˝-bay biplane with fixed underwing 4 -wheel landing gear and tail strut
upper wingtips supported by slanted struts
two spar upper and lower wing
engines, landing gear and fuel attached to the wings, bombload in or attached to fuselage
airscrew :
two fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.63 [ ]
estimated diameter airscrew 2.81 [m]
angle of attack prop : 18.40 [ ]
reduction : 1.00 [ ]
airscrew revs : 1150 [r.p.m.]
pitch at Max speed 2.20 [m]
blade-tip speed at Vmax and max revs. : 174 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.28 [m]
calculated wing chord (rounded tips): 1.38 [m]
wing aspect ratio : 13.43 []
estimated gap : 1.45 [m]
gap/chord : 1.13 [ ]
seize (span*length*height) : 437 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 10.2 [kg/hr]
fuel consumption(cruise speed) : 50.5 [kg/hr] (69.0 [litre/hr]) at 64 [%] power
distance flown for 1 kg fuel : 2.71 [km/kg]
estimated total fuel capacity : 196 [litre] (143 [kg])
calculation : *3* (weight)
weight engine(s) dry : 280.0 [kg] = 1.59 [kg/KW]
weight 39 litre oil tank : 3.3 [kg]
oil tank filled with 1.3 litre oil : 1.2 [kg]
oil in engine 1 litre oil : 0.9 [kg]
fuel in engine 1 litre fuel : 0.9 [kg]
weight 29 litre gravity patrol tank(s) : 4.4 [kg]
weight cowling 3.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 38.0 [kg]
total weight propulsion system : 329 [kg](22.9 [%])
***************************************************************
fuselage skeleton (wood gauge : 7.85 [cm]): 136 [kg]
bracing : 8.8 [kg]
fuselage covering ( 14.0 [m2] doped linen fabric) : 4.5 [kg]
weight controls + indicators: 7.1 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 9.1 [kg]
weight bomb storage : 7.0 [kg]
total weight fuselage : 178 [kg](12.4 [%])
***************************************************************
weight wing covering (doped linen fabric) : 25 [kg]
total weight ribs (92 ribs) : 85 [kg]
weight engine mounts : 9 [kg]
weight two 83 [litre] main fuel tanks empty : 13.3 [kg]
load on front upper spar (clmax) per running metre : 759.6 [N]
load on rear upper spar (vmax) per running metre : 240.3 [N]
total weight 8 spars : 92 [kg]
weight wings : 203 [kg]
weight wing/square meter : 5.10 [kg]
weight 16 interplane struts & cabane : 29.3 [kg]
weight cables (90 [m]) : 13.1 [kg] (= 145 [gram] per metre)
diameter cable : 4.9 [mm]
weight fin & rudder (3.4 [m2]) : 18.1 [kg]
weight stabilizer & elevator (4.5 [m2]): 23.1 [kg]
total weight wing surfaces & bracing : 308 [kg] (21.5 [%])
*******************************************************************
weight machine-gun(s) : 25.4 [kg]
weight pivot mounting mg :6.0 [kg]
weight armament : 31 [kg]
********************************************************************
wheel pressure : 358.8 [kg]
weight 4 wheels (670 [mm] by 79 [mm]) : 33.4 [kg]
weight tailskid : 3.9 [kg]
weight undercarriage with axle 38.5 [kg]
total weight landing gear : 75.9 [kg] (5.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 922 [kg](64.3 [%])
weight oil for 3.0 hours flying : 30.7 [kg]
weight 6 drums empty : 1.2 [kg]
weight ammunition (282 rounds) : 9.0 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 967 [kg] (67.4 [%])
published operational weight empty : 940 [kg] (65.5 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 101 [kg]
********************************************************************
operational weight : 1230 [kg](85.7 [%])
bomb load : 100 [kg]
operational weight bombing mission : 1330 [kg]
weight camera : 20 [kg]
operational weight photo mission : 1250 [kg]
fuel reserve : 42 [kg] enough for 0.84 [hours] flying
possible additional useful load : 143 [kg]
operational weight fully loaded : 1435 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1435 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 6.97 [kg/kW]
total power : 176.5 [kW] at 1150 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.9 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.4 [g]
design flight time : 2.00 [hours]
design cycles : 480 sorties, design hours : 960 [hours]
operational wing loading : 309 [N/m^2]
wing stress (3 g) during operation : 181 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.06 ["]
max. angle of attack (stalling angle) : 9.90 ["]
angle of attack at max. speed : 1.91 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.04 [ ]
lift coefficient at max. speed : 0.28 [ ]
induced drag coefficient at max. speed : 0.0025 [ ]
drag coefficient at max. speed : 0.0606 [ ]
drag coefficient (zero lift) : 0.0581 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 79 [km/u]
landing speed at sea-level (OW without bombload): 95 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 97 [km/hr] at 2362 [m] (power:31 [%])
min. power speed (max range) : 97 [km/hr] at 2362 [m] (power:31 [%])
max. rate of climb speed : 87.6 [km/hr] at sea-level
cruising speed : 137 [km/hr] op 2362 [m] (power:61 [%])
design speed prop : 144 [km/hr]
maximum speed : 152 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 329 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 197 [m]
lift/drag ratio : 11.67 [ ]
max. practical ceiling : 6625 [m] with flying weight :1059 [kg]
practical ceiling (operational weight): 5950 [m] with flying weight :1230 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 5350 [m] with flying weight :1384 [kg]
published ceiling (4725 [m]
climb to 1500m (without bombload) : 5.00 [min]
climb to 3000m (without bombload) : 11.79 [min]
max. dive speed : 369.4 [km/hr] at 4350 [m] height
load factor at max. angle turn 2.60 ["g"]
turn radius at 500m: 56 [m]
time needed for 360* turn 9.7 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.84 [hours] with 2 crew and 163 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 2.50 [hours] with 2 crew and possible useful (bomb) load : 180 [kg] and 88.1 [%] fuel
action radius : 387 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 564 [litre] fuel : 1119 [km]
useful load with action-radius 250km : 229 [kg]
production : 31.30 [tonkm/hour]
oil and fuel consumption per tonkm : 1.94 [kg]
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Literature :
Jane’s Fighting Aircraft WWI page 109
https://www.militaryfactory.com/aircraft/detail.asp?aircraft_id=1276
Wikipedia
http://albindenis.free.fr/Site_escadrille/escadrille056.htm
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 23 November 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4