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Aviatik B.I
role : two-seat unarmed reconnaissance
first flight : start 1914 operational : August 1914
country : Germany
design :
production : unknown, at Leipzig
general information : Aviatik B.I en B.II aircraft were much used in the first months of
WWI at the front. The allied used to call every German aircraft a Taube or an Aviatik.
Not known how many B.I’s were built.
The first German bomber-force, BAO (Brieftaubenabteilung – Ostende), based at Ghistelles (Gistel) was equipped with Aviatik BI aircraft. Begin 1915 it was transferred to the East front. Together with Brieftauben abteilung Metz it operated as mobile tactical bombing force. The fact that the entire unit was housed in railway trains making it easy to switch them from one front to the other.
users : Germany
crew : 2 (observer in front of pilot)
armament : no fixed armament
engine : 1 Mercedes D.I liquid-cooled 6 -cylinder inline engine 100 [hp](73.6 KW)
dimensions :
wingspan : 13.97 [m], length : 7.97 [m], height : 3.3[m]
wing area : 38.0 [m^2]
weights :
max.take-off weight : 1080 [kg]
empty weight operational (estimation): 700.0 [kg] bombload : 50 [kg]
performance :
maximum speed : 100 [km/hr] at sea-level
service ceiling : 4000 [m]
endurance : 4.0 [hours]
estimated action radius : 180 [km]
description :
2½-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
The B.I could be recognized from its swebt-back wings and heart-shaped stabilo
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.62 [ ]
estimated diameter airscrew 2.68 [m]
angle of attack prop : 12.93 [ ]
reduction : 1.00 [ ]
airscrew revs : 1150 [r.p.m.]
pitch at Max speed 1.45 [m]
blade-tip speed at Vmax and max revs. : 164 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.55 [m]
calculated wing chord (rounded tips): 1.72 [m]
wing aspect ratio : 8.99 []
estimated gap : 1.82 [m]
gap/chord : 1.17 [ ]
seize (span*length*height) : 367 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 1.7 [kg/hr]
fuel consumption(cruise speed) : 22.1 [kg/hr] (30.1 [litre/hr]) at 68 [%] power
distance flown for 1 kg fuel : 4.08 [km/kg]
estimated total fuel capacity : 137 [litre] (100 [kg])
calculation : *3* (weight)
weight engine(s) dry : 191.2 [kg] = 2.60 [kg/KW]
weight 11 litre oil tank : 0.9 [kg]
oil tank filled with 0.6 litre oil : 0.5 [kg]
oil in engine 4 litre oil : 3.7 [kg]
fuel in engine 1 litre fuel : 0.4 [kg]
weight 13 litre gravity patrol tank(s) : 1.9 [kg]
weight radiator : 10.5 [kg]
weight exhaust pipes & fuel lines 9.0 [kg]
weight cowling 2.9 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 16.9 [kg]
total weight propulsion system : 237 [kg](22.0 [%])
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fuselage skeleton (wood gauge : 7.04 [cm]): 101 [kg]
bracing : 5.7 [kg]
fuselage covering ( 12.0 [m2] doped linen fabric) : 3.8 [kg]
weight controls + indicators: 6.5 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 3.5 [kg]
weight 124 [litre] main fuel tank empty : 9.9 [kg]
weight engine mounts & firewalls : 4 [kg]
total weight fuselage : 145 [kg](13.4 [%])
***************************************************************
weight wing covering (doped linen fabric) : 24 [kg]
total weight ribs (57 ribs) : 64 [kg]
load on front upper spar (clmax) per running metre : 659.5 [N]
load on rear upper spar (vmax) per running metre : 209.9 [N]
total weight 8 spars : 74 [kg]
weight wings : 162 [kg]
weight wing/square meter : 4.27 [kg]
weight 12 interplane struts & cabane : 44.2 [kg]
weight cables (73 [m]) : 8.5 [kg] (= 116 [gram] per metre)
diameter cable : 4.4 [mm]
weight fin & rudder (2.3 [m2]) : 10.0 [kg]
weight stabilizer & elevator (4.3 [m2]): 18.5 [kg]
total weight wing surfaces & bracing : 244 [kg] (22.6 [%])
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weight armament : 0 [kg]
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wheel pressure : 540.0 [kg]
weight 2 wheels (690 [mm] by 83 [mm]) : 23.0 [kg]
weight tailskid : 2.9 [kg]
weight undercarriage with axle 27.7 [kg]
total weight landing gear : 53.7 [kg] (5.0 [%]
*******************************************************************
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calculated empty weight : 679 [kg](62.9 [%])
weight oil for 4.8 hours flying : 8.1 [kg]
weight cooling fluids : 15.9 [kg]
*******************************************************************
calculated operational weight empty : 703 [kg] (65.1 [%])
estimated operational weight empty : 700 [kg] (64.8 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 44 [kg]
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operational weight : 910 [kg](84.2 [%])
bomb load : 50 [kg]
operational weight bombing mission : 960 [kg]
weight camera : 20 [kg]
operational weight photo mission : 930 [kg]
fuel reserve : 56 [kg] enough for 2.54 [hours] flying
possible additional useful load : 94 [kg]
operational weight fully loaded : 1080 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1080 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 12.37 [kg/kW]
total power : 73.6 [kW] at 1150 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.3 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] loadfactor : 2.4 [g]
design flight time : 3.20 [hours]
design cycles : 375 sorties, design hours : 1200 [hours]
operational wing loading : 240 [N/m^2]
wing stress (3 g) during operation : 169 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.14 ["]
max.angle of attack (stalling angle) : 11.82 ["]
angle of attack at max.speed : 4.57 ["]
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 : 0.50 [ ]
induced drag coefficient at max.speed : 0.0119 [ ]
drag coefficient at max.speed : 0.0915 [ ]
drag coefficient (zero lift) : 0.0797 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 66 [km/u]
landing speed at sea-level (OW without bombload): 79 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 80 [km/hr] at 2000 [m] (power:57 [%])
min. power speed (max range) : 80 [km/hr] at 2000 [m] (power:57 [%])
cruising speed : 90 [km/hr] op 2000 [m] (power:69 [%])
design speed prop : 95 [km/hr]
maximum speed : 100 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 144 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 218 [m]
lift/drag ratio : 8.15 [ ]
max. practical ceiling : 3950 [m] with flying weight :796 [kg]
practical ceiling (operational weight): 3125 [m] with flying weight :910 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2075 [m] with flying weight :1058 [kg]
published ceiling (4000 [m]
climb to 1500m (without bombload) : 12.12 [min]
max.dive speed : 235.5 [km/hr] at 1075 [m] height
load factor at max.angle turn 1.58 ["g"]
turn radius at 500m: 47 [m]
time needed for 360* turn 12.5 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 4.54 [hours] with 2 crew and 114 [kg] useful (bomb)load
published endurance : 4.00 [hours] with 2 crew and useful (bomb) load : 126 [kg]
action radius : 397 [km] with 2 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 403 [litre] fuel : 1206 [km]
useful load with action-radius 250km : 173 [kg]
production : 15.57 [tonkm/hour]
oil and fuel consumption per tonkm : 1.53 [kg]
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Literature :
Praktisch handboek vliegtuigen deel 1 page 250,297
Warplanes of WOI page 12,15,36,66
Bombers 1914-19 page109
German aircraft of the first world war page 279
Jane’s fighting aircraft WWI page 218
http://fandavion.free.fr
last check python :
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(32-bit)