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weight and performance calculations for the Albatros C.VII
Albatros C.VII
role : multi role combat aircraft
first flight : operational : December 1916
country : Germany
design :
production : 400 aircraft
general information :
Due to engine problems with the Mercedes straight-eight, it was decided to take back
the reliable Benz Bz IV of 200 hp for the next model.
One took over the good points of the C. V and this led to the C. VII.
This model became very popular. Could keep up against a SE5 at 3000m altitude.
users : Luftwaffe
crew : 2
armament : 1 synchronized 7.92 [mm] (0.312 in) Spandau LMG 08/15 machine-gun
and 1 movable 7.92 [mm] (0.312 in) Parabellum MG 14 machine-gun for the observer
engine : 1 Benz Bz.IV liquid-cooled 6 -cylinder inline engine 220 [hp](161.8 KW)
dimensions :
wingspan : 12.78 [m], length : 8.7 [m], height : 3.8[m]
wing area : 43.4 [m^2]
weights :
max.take-off weight : 1550 [kg]
empty weight operational : 989 [kg] bombload : 90 [kg]
performance :
maximum speed : 170 [km/hr] at sea-level
climbing speed : 192 [m/min]
service ceiling : 5000 [m]
endurance : 3.33 [hours]
estimated action radius : 255 [km]
description :
2-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
engines, landing gear, fuel and bombs in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.63 [ ]
estimated diameter airscrew 2.98 [m]
angle of attack prop : 16.08 [ ]
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 2.02 [m]
blade-tip speed at Vmax and max revs. : 223 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.70 [m]
calculated wing chord (rounded tips): 1.88 [m]
wing aspect ratio : 7.53 []
estimated gap : 1.70 [m]
gap/chord : 1.00 [ ]
seize (span*length*height) : 423 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.1 [kg/hr]
fuel consumption(cruise speed) : 35.9 [kg/hr] (49.0 [litre/hr]) at 63 [%] power
distance flown for 1 kg fuel : 4.26 [km/kg]
estimated total fuel capacity : 185 [litre] (136 [kg])
calculation : *3* (weight)
weight engine(s) dry : 370.0 [kg] = 2.29 [kg/KW]
weight 13 litre oil tank : 1.1 [kg]
oil tank filled with 1.2 litre oil : 1.1 [kg]
oil in engine 9 litre oil : 8.1 [kg]
fuel in engine 1 litre fuel : 0.8 [kg]
weight 21 litre gravity patrol tank(s) : 3.1 [kg]
weight radiator : 24.3 [kg]
weight exhaust pipes & fuel lines 14.4 [kg]
weight self-starter : 4.0 [kg]
weight cowling 6.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 24.3 [kg]
total weight propulsion system : 456 [kg](29.5 [%])
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fuselage skeleton (wood gauge : 6.93 [cm]): 107 [kg]
bracing : 6.6 [kg]
fuselage covering ( 14.3 [m2] doped linen fabric) : 4.6 [kg]
weight controls + indicators: 6.5 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 6.3 [kg]
weight bomb sight : 1.0 [kg]
weight 164 [litre] main fuel tank empty : 13.1 [kg]
weight oxygen/compressed air flasks for high altitude : 7.2 [kg]
weight engine mounts & firewalls : 8 [kg]
total weight fuselage : 171 [kg](11.1 [%])
***************************************************************
weight wing covering (doped linen fabric) : 28 [kg]
total weight ribs (75 ribs) : 92 [kg]
load on front upper spar (clmax) per running metre : 712.3 [N]
load on rear upper spar (vmax) per running metre : 335.5 [N]
total weight 8 spars : 67 [kg]
weight wings : 187 [kg]
weight wing/square meter : 4.30 [kg]
weight 8 interplane struts & cabane : 23.3 [kg]
weight cables (75 [m]) : 7.9 [kg] (= 105 [gram] per metre)
diameter cable : 4.1 [mm]
weight fin & rudder (1.9 [m2]) : 8.4 [kg]
weight stabilizer & elevator (4.9 [m2]): 21.3 [kg]
total weight wing surfaces & bracing : 247 [kg] (16.0 [%])
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weight machine-gun(s) : 26.5 [kg]
weight pivot mounting mg :6.9 [kg]
weight ammunition magazine(s) :2.3 [kg]
weight Fokker Stangensteuerung synchronization gear : 1.0 [kg]
Benz B.IV and synchronized MG
weight armament : 37 [kg]
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wheel pressure : 775.0 [kg]
weight 2 wheels (760 [mm] by 100 [mm]) : 31.6 [kg]
weight tailskid : 2.8 [kg]
weight undercarriage with axle 30.4 [kg]
total weight landing gear : 64.8 [kg] (4.2 [%]
*******************************************************************
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calculated empty weight : 977 [kg](63.0 [%])
weight oil for 4.0 hours flying : 8.4 [kg]
weight cooling fluids : 35.0 [kg]
weight 1 drums empty : 2.3 [kg]
weight ammunition (1000 rounds) : 30.5 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 1056 [kg] (68.1 [%])
published operational weight empty : 989 [kg] (63.8 [%])
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weight crew : 162 [kg]
weight (electrical heated) clothing for high altitude : 12.0 [kg]
weight fuel for 2.0 hours flying : 72 [kg]
********************************************************************
operational weight : 1301 [kg](84.0 [%])
bomb load : 90 [kg]
operational weight bombing mission : 1391 [kg]
fuel reserve : 64 [kg] enough for 1.78 [hours] flying
possible additional useful load : 95 [kg]
operational weight fully loaded : 1550 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1550 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 8.04 [kg/kW]
total power : 161.8 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.1 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 1.6 [g]
design flight time : 2.66 [hours]
design cycles : 188 sorties, design hours : 500 [hours]
operational wing loading : 294 [N/m^2]
wing stress (3 g) during operation : 205 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.19 ["]
max. angle of attack (stalling angle) : 12.43 ["]
angle of attack at max. speed : 1.39 ["]
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 : 0.22 [ ]
induced drag coefficient at max. speed : 0.0036 [ ]
drag coefficient at max. speed : 0.0363 [ ]
drag coefficient (zero lift) : 0.0328 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 74 [km/u]
landing speed at sea-level (OW without bombload): 88 [km/hr]
min. drag speed (max endurance) : 110 [km/hr] at 2500 [m](power :42 [%])
min. power speed (max range) : 118 [km/hr] at 2500 [m] (power:44 [%])
max. rate of climb speed : 104.0 [km/hr] at sea-level
cruising speed : 153 [km/hr] op 2500 [m] (power:65 [%])
design speed prop : 162 [km/hr]
maximum speed : 170 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 246 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 168 [m]
lift/drag ratio : 10.07 [ ]
max. practical ceiling : 5425 [m] with flying weight :1119 [kg]
practical ceiling (operational weight): 4575 [m] with flying weight :1301 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 3650 [m] with flying weight :1514 [kg]
published ceiling (5000 [m]
climb to 1500m (without bombload) : 6.86 [min]
climb to 3000m (without bombload) : 17.26 [min]
max. dive speed : 394.9 [km/hr] at 2650 [m] height
load factor at max. angle turn 1.97 ["g"]
turn radius at 500m: 52 [m]
time needed for 360* turn 11.1 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 3.78 [hours] with 2 crew and 197 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 3.33 [hours] with 2 crew and possible useful (bomb) load : 213 [kg] and 88.1 [%] fuel
action radius : 666 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 625 [litre] fuel : 1952 [km]
useful load with action-radius 250km : 341 [kg]
production : 52.16 [tonkm/hour]
oil and fuel consumption per tonkm : 0.73 [kg]
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Literature :
Praktisch handboek vliegtuigen deel 1 page 264
Warplanes WOI page 59,61,97
Jane’s fighting aircraft page 146
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 23 September 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4