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weight and performance calculations for the Aviatik B.II series 32
Aviatik B.II series 32
role : two-seat unarmed reconnaissance
importance : ***
first flight : 1914 operational : spring 1915
country : Austria
design : more then 48 in Vienna
production : 48 aircraft
general information :
Variant of the B.I. Built in Germany is widely used by the Luftwaffe and the Austrians until 1916. It had a stronger engine and another tail. On October 5, 1914, a Voisin III shoots an Aviatik B.II with his mitrailleur, 1st time that this succeeds with a mitrailleur. Given the date, I think this was an Aviatik B.I. or Albatros B.II ??
users : Austria, Germany
crew : 2
armament : no fixed armament
engine : 1 Austro-Daimler liquid-cooled 6 -cylinder inline engine 120 [hp](88.3 KW)
dimensions :
wingspan : 12.35 [m], length : 8.0 [m], height : 3.15[m]
wing area : 35.2 [m^2]
weights :
max.take-off weight : 1088 [kg]
empty weight operational : 730 [kg] bombload : 75 [kg]
performance :
maximum speed : 109 [km/hr] at sea-level
climbing speed : 96 [m/min]
service ceiling : 3000 [m]
endurance : 4.0 [hours]
estimated action radius : 196 [km]
description :
2˝-bay biplane with fixed landing gear and tail strut
upper wingtips supported by slanted struts
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 2.32 [m]
angle of attack prop : 15.48 [ ]
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.51 [m]
blade-tip speed at Vmax and max revs. : 149 [m/s]
The B.II has a more straight wing compared to the more arrow-shaped wing of the B.I
calculation : *1* (dimensions)
mean wing chord : 1.63 [m]
calculated wing chord (rounded tips): 1.83 [m]
wing aspect ratio : 7.58 []
estimated gap : 1.67 [m]
gap/chord : 1.03 [ ]
seize (span*length*height) : 311 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.2 [kg/hr]
fuel consumption(cruise speed) : 26.4 [kg/hr] (36.1 [litre/hr]) at 72 [%] power
distance flown for 1 kg fuel : 3.71 [km/kg]
estimated total fuel capacity : 164 [litre] (120 [kg])
calculation : *3* (weight)
weight engine(s) dry : 247.0 [kg] = 2.80 [kg/KW]
weight 14 litre oil tank : 1.2 [kg]
oil tank filled with 0.7 litre oil : 0.6 [kg]
oil in engine 5 litre oil : 4.4 [kg]
fuel in engine 1 litre fuel : 0.4 [kg]
weight 15 litre gravity patrol tank(s) : 2.3 [kg]
weight radiator : 12.6 [kg]
weight exhaust pipes & fuel lines 10.9 [kg]
weight cowling 3.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 301 [kg](27.6 [%])
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fuselage skeleton (wood gauge : 6.83 [cm]): 96 [kg]
bracing : 5.4 [kg]
fuselage covering ( 12.1 [m2] doped linen fabric) : 3.9 [kg]
weight controls + indicators: 6.3 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 5.3 [kg]
weight 148 [litre] main fuel tank empty : 11.9 [kg]
weight engine mounts & firewalls : 4 [kg]
total weight fuselage : 144 [kg](13.2 [%])
***************************************************************
weight wing covering (doped linen fabric) : 23 [kg]
total weight ribs (55 ribs) : 65 [kg]
load on front upper spar (clmax) per running metre : 703.1 [N]
load on rear upper spar (vmax) per running metre : 239.2 [N]
total weight 8 spars : 61 [kg]
weight wings : 149 [kg]
weight wing/square meter : 4.22 [kg]
weight 12 interplane struts & cabane : 32.9 [kg]
weight cables (67 [m]) : 6.5 [kg] (= 97 [gram] per metre)
diameter cable : 4.0 [mm]
weight fin & rudder (1.8 [m2]) : 7.7 [kg]
weight stabilizer & elevator (4.0 [m2]): 17.0 [kg]
total weight wing surfaces & bracing : 213 [kg] (19.6 [%])
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weight armament : 0 [kg]
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wheel pressure : 544.0 [kg]
weight 2 wheels (700 [mm] by 82 [mm]) : 23.7 [kg]
weight tailskid : 2.8 [kg]
weight undercarriage with axle 25.9 [kg]
total weight landing gear : 52.3 [kg] (4.8 [%]
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has sloping styles to the top wing. Looking at the registration 34.07 and what the cockpit looks like this is an Aviatik B.II
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calculated empty weight : 710 [kg](65.2 [%])
weight oil for 4.8 hours flying : 10.6 [kg]
weight cooling fluids : 19.1 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 740 [kg] (68.1 [%])
published operational weight empty : 730 [kg] (67.1 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 53 [kg]
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operational weight : 955 [kg](87.8 [%])
bomb load : 75 [kg]
operational weight bombing mission : 1030 [kg]
weight camera : 20 [kg]
operational weight photo mission : 975 [kg]
fuel reserve : 67 [kg] enough for 2.54 [hours] flying
possible additional useful load : 46 [kg]
operational weight fully loaded : 1088 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1088 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 10.82 [kg/kW]
total power : 88.3 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.4 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.2 [g]
design flight time : 3.20 [hours]
design cycles : 328 sorties, design hours : 1050 [hours]
operational wing loading : 272 [N/m^2]
Aviatik B.II with slanted struts to the wing tips
wing stress (3 g) during operation : 193 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.18 ["]
max. angle of attack (stalling angle) : 12.40 ["]
angle of attack at max. speed : 4.48 ["]
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 : 0.48 [ ]
induced drag coefficient at max. speed : 0.0128 [ ]
drag coefficient at max. speed : 0.0921 [ ]
drag coefficient (zero lift) : 0.0792 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 70 [km/u]
landing speed at sea-level (OW without bombload): 84 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 83 [km/hr] at 1500 [m] (power:55 [%])
min. power speed (max range) : 83 [km/hr] at 1500 [m] (power:55 [%])
cruising speed : 98 [km/hr] op 1500 [m] (power:71 [%])
design speed prop : 104 [km/hr]
maximum speed : 109 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 163 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 260 [m]
lift/drag ratio : 7.51 [ ]
max. practical ceiling : 3900 [m] with flying weight :833 [kg]
practical ceiling (operational weight): 3100 [m] with flying weight :955 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2400 [m] with flying weight :1062 [kg]
published ceiling (3000 [m]
climb to 1500m (without bombload) : 10.83 [min]
max. dive speed : 264.7 [km/hr] at 1400 [m] height
load factor at max. angle turn 1.58 ["g"]
turn radius at 500m: 53 [m]
time needed for 360* turn 13.3 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 4.18 [hours] with 2 crew and 75 [kg] useful (bomb)load and 92.1 [%] fuel
published endurance : 4.00 [hours] with 2 crew and possible useful (bomb) load : 80 [kg] and 88.1 [%] fuel
action radius : 307 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 365 [litre] fuel : 993 [km]
useful load with action-radius 250km : 133 [kg]
production : 13.05 [tonkm/hour]
oil and fuel consumption per tonkm : 2.20 [kg]
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Literature :
Praktisch handboek vliegtuigen deel 1 page 250,297
Bombers 1914-19 page 32
Forum.valka.cz
German aircraft of world war one page 280df
Jane’s fighting aircraft WWI page 144
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 23 November 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4