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Aviatik (Berg) D.I WWI fighter biplane weight and performance calculations

Aviatik (Berg) D.1

role : fighter

first flight : operational : October 1917

country : Austria

design : Julius von Berg

production : 700 aircraft

general information :

users : Austria

crew : 1

armament : 2 synchronized 8.00 [mm] (0.315 in) Schwarzlose M.7 machine-guns

engine : 1 Austro-Daimler liquid-cooled 6 -cylinder inline engine 200 [hp](147.1 KW)

dimensions :

wingspan : 8.0 [m], length : 6.86 [m], height : 2.49[m]

wing area : 21.8 [m^2]

weights :

max.take-off weight : 881 [kg]

empty weight operational : 669 [kg] bombload : 0 [kg]

performance :

maximum speed : 185 [km/hr] at sea-level

service ceiling : 6220 [m]

estimated endurance : 1.65 [hours]

estimated action radius : 137 [km]

description :

1-bay biplane with fixed landing gear and tail strut

two spar upper en lower wing

airscrew :

fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.64 [ ]

estimated diameter airscrew 2.63 [m]

angle of attack prop : 19.57 [ ]

reduction : none

airscrew revs : 1400 [r.p.m.]

pitch at Max speed 2.20 [m]

blade-tip speed at Vmax and max revs. : 200 [m/s]

calculation : *1* (dimensions)

mean wing chord : 1.36 [m]

wing aspect ratio : 5.87 []

estimated gap : 1.25 [m]

gap/chord : 0.92 [ ]

seize (span*length*height) : 137 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 3.5 [kg/hr]

fuel consumption(cruise speed) : 29.4 [kg/hr] (40.2 [litre/hr]) at 62 [%] power

distance flown for 1 kg fuel : 5.65 [km/kg]

estimated total fuel capacity : 75 [litre] (55 [kg])

calculation : *3* (weight)

weight engine(s) dry : 330.0 [kg] = 2.24 [kg/KW]

weight 11 litre oil tank : 1.0 [kg]

oil tank filled with 1.1 litre oil : 1.0 [kg]

oil in engine 8 litre oil : 7.4 [kg]

fuel in engine 1 litre fuel : 0.7 [kg]

weight 17 litre gravity patrol tank(s) : 2.6 [kg]

weight radiator : 21.1 [kg]

weight exhaust pipes & fuel lines 6.8 [kg]

weight self-starter : 3.6 [kg]

weight cowling 5.9 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 22.1 [kg]

total weight propulsion system : 401 [kg](45.5 [%])

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fuselage skeleton (wood gauge : 5.00 [cm]): 44 [kg]

bracing : 2.1 [kg]

fuselage covering ( 8.9 [m2] doped linen fabric) : 2.8 [kg]

weight controls + indicators: 5.4 [kg]

weight seats : 3.0 [kg]

weight other details, lighting set, etc. : 5.1 [kg]

weight 58 [litre] main fuel tank empty : 4.7 [kg]

weight engine mounts & firewalls : 7 [kg]

total weight fuselage : 74 [kg](8.4 [%])

***************************************************************

weight wing covering (doped linen fabric) : 14 [kg]

total weight ribs (53 ribs) : 52 [kg]

load on front upper spar (clmax) per running metre : 620.9 [N]

load on rear upper spar (vmax) per running metre : 319.3 [N]

total weight 8 spars : 23 [kg]

weight wings : 89 [kg]

weight wing/square meter : 4.09 [kg]

weight 4 interplane struts & cabane : 5.4 [kg]

weight cables (40 [m]) : 1.4 [kg] (= 36 [gram] per metre)

diameter cable : 2.4 [mm]

weight fin & rudder (0.7 [m2]) : 3.1 [kg]

weight stabilizer & elevator (2.5 [m2]): 10.2 [kg]

total weight wing surfaces & bracing : 109 [kg] (12.4 [%])

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weight machine-gun(s) : 30.0 [kg]

weight machine gun-mounting top plane : 1.5 [kg]

weight ammunition magazine(s) :3.5 [kg]

weight armament : 35 [kg]

********************************************************************

wheel pressure : 440.5 [kg]

weight 2 wheels (790 [mm] by 99 [mm]) : 18.8 [kg]

weight tailskid : 1.5 [kg]

weight undercarriage with axle 14.9 [kg]

total weight landing gear : 35.1 [kg] (4.0 [%]

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calculated empty weight : 655 [kg](74.3 [%])

weight oil for 2.0 hours flying : 7.0 [kg]

weight cooling fluids : 31.8 [kg]

weight ammunition (1000 rounds) : 35.3 [kg]

weight signal pistol with cartridges : 3.6 [kg]

*******************************************************************

calculated operational weight empty : 733 [kg] (83.2 [%])

published operational weight empty : 669 [kg] (75.9 [%])

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weight crew : 81 [kg]

weight fuel for 1.5 hours flying : 44 [kg]

********************************************************************

operational weight : 858 [kg](97.4 [%])

bombload could not be carried with fuel for 2 hours flying time

fuel reserve : 11 [kg] enough for 0.37 [hours] flying

possible additional useful load : 12 [kg]

operational weight fully loaded : 881 [kg] with fuel tank filled for 100 [%]

published maximum take-off weight : 881 [kg] (100.0 [%])

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calculation : * 4 * (engine power)

power loading (operational without bombload) : 5.83 [kg/kW]

total power : 147.1 [kW] at 1400 [r.p.m]

calculation : *5* (loads)

manoeuvre load : 2.7 [g] at 1000 [m]

limit load : 4.5 [g]

design flight time : 1.32 [hours]

design cycles : 155 sorties, design hours : 205 [hours]

operational wing loading : 386 [N/m^2]

wing stress (3 g) during operation : 283 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.27 ["]

max.angle of attack (stalling angle) : 13.08 ["]

angle of attack at max.speed : 1.79 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° :0.10 [ ]

lift coefficient at max. angle of attack : 1.13 [ ]

lift coefficient at max.speed : 0.24 [ ]

induced drag coefficient at max.speed : 0.0056 [ ]

drag coefficient at max.speed : 0.0515 [ ]

drag coefficient (zero lift) : 0.0459 [ ]

Aviatik Berg DI CRETL

calculation : *8* (speeds

stalling speed at sea-level (OW): 85 [km/u]

landing speed at sea-level (OW without bombload): 102 [km/hr]

min.drag speed (max endurance) : 127 [km/hr] at 3110 [m](power :46 [%])

min. power speed (max range) : 138 [km/hr] at 3110 [m] (power:49 [%])

max.rate of climb speed : 114.5 [km/hr] at sea-level

cruising speed : 166 [km/hr] op 3110 [m] (power:64 [%])

design speed prop : 179 [km/hr]

maximum speed : 185 [km/hr] op 100 [m] (power:99 [%])

climbing speed at sea-level (without bombload) : 325 [m/min]

calculation : *9* (regarding various performances)

take-off distance at sea-level : 156 [m]

lift/drag ratio : 7.52 [ ]

max. practical ceiling : 5700 [m] with flying weight :789 [kg]

practical ceiling (operational weight): 5125 [m] with flying weight :858 [kg]

practical ceiling fully loaded (mtow- 1 hour fuel) : 5175 [m] with flying weight :852 [kg]

published ceiling (6220 [m]) vmin : 117.4 [km/hr] vmax : 117.4 [km/hr]

climb to 1500m (without bombload) : 5.15 [min]

climb to 3000m (without bombload) : 12.62 [min]

max.dive speed : 420.9 [km/hr] at 4175 [m] height

load factor at max.angle turn 1.89 ["g"]

turn radius at 500m: 71 [m]

time needed for 360* turn 13.3 [seconds] at 500m

calculation *10* (action radius & endurance)

operational endurance : 1.61 [hours] with 1 crew and 20 [kg] useful load and 86.0 [%] fuel

published endurance : 1.65 [hours] with 1 crew and possible useful (bomb) load : 19 [kg]

action radius : 134 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload

max range theoretically with additional fuel tanks for total 145 [litre] fuel : 601 [km]

useful load with action-radius 250km : 18 [kg]

production : 2.98 [tonkm/hour]

oil and fuel consumption per tonkm : 11.06 [kg]

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IMPORTANTIE : 3

Literatuur : wikepedia

Praktisch handbook vliegtuigen deel 1

http://www.theaerodrome.com

fighters 1914-19

Journal – Flight for 1918

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/photograps/content please mail to below mail address

(c) B van der Zalm 30 november 2018 contact : bvanderzalm@ziggo.nl python 3.4.1