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weight and performance calculations for the Albatros B.III
Albatros B.III
role : two-seat unarmed reconnaissance
importance : **
first flight : operational : April 1915
country : Germany
design :
production : unknown
general information :
improved version of the B.II, with modified tail surfaces and a smaller wingspan. However, it quickly became clear that the unarmed two-seat reconnaissance airplanes became too vulnerable to the allied fighters equipped with machine guns that now appeared at the front. It was replaced by the armed C version after a short time. It was withdrawn from the front and deployed as a training aircraft.
users : Germany
crew : 2
armament : no fixed armament
engine : 1 Mercedes D.II liquid-cooled 6 -cylinder inline engine 120 [hp](89.5 KW)
dimensions :
wingspan : 11.0 [m], length : 7.8 [m], height : 3.15[m]
wing area : 36.84 [m^2]
weights :
max.take-off weight : 1071 [kg]
empty weight operational : 723 [kg] bombload : 0 [kg]
performance :
maximum speed : 120 [km/hr] at sea-level
service ceiling : 3000 [m]
endurance : 4.0 [hours]
estimated action radius : 216 [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 [ ]
diameter airscrew 2.74 [m]
angle of attack prop : 12.48 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 1.43 [m]
blade-tip speed at Vmax and max revs. : 204 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.67 [m]
calculated wing chord (rounded tips): 1.88 [m]
wing aspect ratio : 6.57 []
gap : 1.52 [m]
gap/chord : 0.91 [ ]
seize (span*length*height) : 270 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.1 [kg/hr]
fuel consumption(cruise speed) : 23.8 [kg/hr] (32.4 [litre/hr]) at 73 [%] power
distance flown for 1 kg fuel : 4.54 [km/kg]
estimated total fuel capacity : 147 [litre] (108 [kg])
calculation : *3* (weight)
weight engine(s) dry : 204.0 [kg] = 2.28 [kg/KW]
weight 13 litre oil tank : 1.7 [kg]
oil tank filled with 0.7 litre oil : 0.6 [kg]
oil in engine 5 litre oil : 4.5 [kg]
fuel in engine 1 litre fuel : 0.4 [kg]
weight 14 litre gravity patrol tank(s) : 1.4 [kg]
weight radiator : 12.8 [kg]
weight exhaust pipes & fuel lines 11.5 [kg]
weight cowling 3.6 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 258 [kg](24.1 [%])
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fuselage skeleton (wood gauge : 7.64 [cm]): 117 [kg]
bracing : 6.4 [kg]
fuselage covering ( 11.5 [m2] doped linen fabric) : 3.7 [kg]
weight controls + indicators: 6.1 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight transceiver : 27 [kg]
weight 134 [litre] main fuel tank empty : 12.8 [kg]
weight engine mounts & firewalls : 4 [kg]
total weight fuselage : 188 [kg](17.6 [%])
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weight wing covering (doped linen fabric) : 24 [kg]
total weight ribs (52 ribs) : 64 [kg]
load on front upper spar (clmax) per running metre : 988.5 [N]
load on rear upper spar (vmax) per running metre : 264.3 [N]
total weight 8 spars : 69 [kg]
weight wings : 156 [kg]
weight wing/square meter : 4.23 [kg]
weight 8 interplane struts & cabane : 18.2 [kg]
weight cables (66 [m]) : 7.1 [kg] (= 108 [gram] per metre)
diameter cable : 4.2 [mm]
weight fin & rudder (1.4 [m2]) : 6.1 [kg]
weight stabilizer & elevator (4.1 [m2]): 17.8 [kg]
total weight wing surfaces & bracing : 205 [kg] (19.1 [%])
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weight armament : 0 [kg]
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wheel pressure : 535.5 [kg]
weight 2 wheels (700 [mm] by 84 [mm]) : 22.9 [kg]
weight tailskid : 3.4 [kg]
weight undercarriage with axle 31.7 [kg]
total weight landing gear : 58.1 [kg] (5.4 [%]
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On 1 December 1915 a Albatros B.III, s/n B 876-1915 nr.940 landed near Aardenburg, the Netherlands. It was interned by the Dutch and given registration LA28. It had a wireless set which was copied by the Dutch and used from April 1917.
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calculated empty weight : 709 [kg](66.2 [%])
weight oil for 4.8 hours flying : 9.9 [kg]
weight cooling fluids : 18.4 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 739 [kg] (69.0 [%])
published operational weight empty : 723 [kg] (67.5 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 48 [kg]
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operational weight : 948 [kg](88.5 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 998 [kg]
weight camera : 20 [kg]
operational weight photo mission : 968 [kg]
fuel reserve : 60 [kg] enough for 2.54 [hours] flying
possible additional useful load : 42 [kg]
operational weight fully loaded : 1071 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1071 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 10.60 [kg/kW]
total power : 89.5 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.7 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.8 [g]
design flight time : 3.20 [hours]
design cycles : 531 sorties, design hours : 1700 [hours]
operational wing loading : 258 [N/m^2]
wing stress (3 g) during operation : 183 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.23 ["]
max. angle of attack (stalling angle) : 12.81 ["]
angle of attack at max. speed : 3.38 ["]
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 : 0.37 [ ]
induced drag coefficient at max. speed : 0.0121 [ ]
drag coefficient at max. speed : 0.0669 [ ]
drag coefficient (zero lift) : 0.0548 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 68 [km/u]
landing speed at sea-level (OW without bombload): 82 [km/hr]
min. drag speed (max endurance) : 88 [km/hr] at 1500 [m](power :59 [%])
min. power speed (max range) : 98 [km/hr] at 1500 [m] (power:65 [%])
max. rate of climb speed : 78.9 [km/hr] at sea-level
cruising speed : 108 [km/hr] op 1500 [m] (power:74 [%])
design speed prop : 114 [km/hr]
maximum speed : 120 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 147 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 122 [m]
lift/drag ratio : 7.28 [ ]
max. practical ceiling : 3675 [m] with flying weight :830 [kg]
practical ceiling (operational weight) : 2800 [m] with flying weight :948 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 2100 [m] with flying weight :1047 [kg]
published ceiling (3000 [m]
climb to 1500m (operational weight without bombload) : 12.19 [min]
max. dive speed : 276.6 [km/hr] at 1100 [m] height
load factor at max. angle turn 1.49 ["g"]
turn radius at 500m: 53 [m]
time needed for 360* turn 14.0 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 4.54 [hours] with 2 crew and 62 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 4.00 [hours] with 2 crew and possible useful (bomb) load : 75 [kg] and 88.1 [%] fuel
action radius : 342 [km] with 2 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 345 [litre] fuel : 1147 [km]
useful load with action-radius 250km : 143 [kg]
production : 15.39 [tonkm/hour]
oil and fuel consumption per tonkm : 1.68 [kg]
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Literature :
Praktisch handboek vliegtuigen deel 1 page 262
Bombers 1914-19 page 109
German aircraft of the first world war page 252
Van Brik tot Starfighter page 24,26,29
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 28 June 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4