weight and performance calculations and info for world war one aircraft for comparison and evaluation added with photographs
weight and performance calculations for the AEG G.IV WWI medium-weight bomber biplane
AEG G.IV
role : medium-weight bomber
importance : ****
first flight : operational : december 1916
country : Germany
design :
production : 400 aircraft
general information : The G.IV entered service at the end of 1916. It was a further development of its predecessors, The G.I, G.II and G.III.
The G.IV had the same structure as the G.III it differed mainly in the use of the more reliabel Mercedes D.IVa engines. This version was the most used variant.
It had a limited range and the ceiling was low, for this reason the G.IV was used for tactical missions. It reamined in service till the end of WWI.
The fueltanks were located beneath and direct behind the pilot. Bombs were carried partly in the fuselage and partly under the wingroots
airscrew diameter : 3.14 [m] pitch : 1.51 [m]
Steel (tubes) was widely used in the constructions, also in the wings.
Petrol capacity : 123 gallons = 559 litre = 410 kg, endurance : 4.5 hrs
Two main petrol tanks, each 270 litre placed under the pilot’s seat, 2 gravity tanks in the upper plane
Oil capacity : 11 gallons = 50 litre = 44.9 kg
Water capacity : 13 gallons = 59.1 litre
Climb to 1524m : 10.3 mins landing speed = 75-80 km/u (mph ??)
users : Germany
crew : 3
armament : 3 movable 7.92 [mm] (0.312 in) Parabellum MG 14 machine-guns
engine : 2 Mercedes D.IVa liquid-cooled 6-cylinder inline engine 252 [hp](185.3 KW)
dimensions :
wingspan : 18.34 [m], length : 9.85 [m], height : 3.89[m]
wing area : 67.85 [m^2]
weights :
max.take-off weight : 3626 [kg]
empty weight operational : 2400 [kg] bombload : 350 [kg]
performance :
maximum speed : 165 [km/hr] at sea-level
climbing speed : 119 [m/min]
service ceiling : 3993 [m]
endurance : 3.685 [hours]
estimated action radius : 274 [km]
description :
2-bay biplane with fixed underwing 4 -wheel landing gear and tail strut
two spar upper and lower wing
engines and landing gear attached to the wings, fuel and bombload in or attached
to fuselage
airscrew :
two fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.63 [ ]
diameter airscrew 3.14 [m]
angle of attack prop : 14.87 [ ]
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 1.96 [m]
blade-tip speed at Vmax and max revs. : 235 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.85 [m]
calculated wing chord (rounded tips): 1.99 [m]
wing aspect ratio : 9.91 []
estimated gap : 2.29 [m]
gap/chord : 1.24 [ ]
seize (span*length*height) : 703 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 8.5 [kg/hr]
fuel consumption(cruise speed) : 98.0 [kg/hr] (133.6 [litre/hr]) at 74 [%] power
distance flown for 1 kg fuel : 1.52 [km/kg]
estimated total fuel capacity : 559 [litre] (410 [kg])
calculation : *3* (weight)
weight engine(s) dry : 850.0 [kg] = 2.29 [kg/KW]
weight 51 litre oil tank : 4.4 [kg]
oil tank filled with 2.8 litre oil : 2.5 [kg]
oil in engine 21 litre oil : 18.5 [kg]
fuel in engine 3 litre fuel : 1.9 [kg]
weight 57 litre gravity patrol tank(s) : 8.5 [kg]
weight radiator : 55.6 [kg]
weight exhaust pipes & fuel lines 19.5 [kg]
weight self-starter : 4.5 [kg]
weight cowling 7.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 55.6 [kg]
total weight propulsion system : 1024 [kg](28.2 [%])
***************************************************************
fuselage skeleton (wood gauge : 11.15 [cm]): 314 [kg]
bracing : 21.8 [kg]
fuselage covering ( 18.3 [m2] doped linen fabric) : 5.9 [kg]
weight controls + indicators: 7.5 [kg]
weight seats : 9.0 [kg]
weight other details, lighting set, etc. : 9.1 [kg]
weight bomb storage : 24.5 [kg]
weight two 251 [litre] main fuel tanks empty : 40.2 [kg]
weight interior + equipment + fuel lines: 55 [kg]
total weight fuselage : 486 [kg](13.4 [%])
***************************************************************
weight wing covering (doped linen fabric) : 43 [kg]
total weight ribs (160 ribs) : 216 [kg]
weight engine mounts : 19 [kg]
load on front upper spar (clmax) per running metre : 1304.0 [N]
load on rear upper spar (vmax) per running metre : 554.8 [N]
total weight 8 spars : 170 [kg]
weight wings : 429 [kg]
weight wing/square meter : 6.32 [kg]
weight 8 interplane struts & cabane : 92.2 [kg]
weight cables (103 [m]) : 31.9 [kg] (= 308 [gram] per metre)
diameter cable : 7.1 [mm]
weight fin & rudder (3.9 [m2]) : 25.3 [kg]
weight stabilizer & elevator (7.6 [m2]): 48.8 [kg]
total weight wing surfaces & bracing : 646 [kg] (17.8 [%])
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weight machine-gun(s) : 28.5 [kg]
weight pivot mounting mg :10.0 [kg]
weight armament : 38 [kg]
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wheel pressure : 906.5 [kg]
weight 4 wheels (840 [mm] by 129 [mm]) : 96.7 [kg]
weight tailskid : 7.3 [kg]
weight undercarriage with axle 88.8 [kg]
total weight landing gear : 192.9 [kg] (5.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 2387 [kg](65.8 [%])
weight oil for 4.4 hours flying : 37.7 [kg]
weight cooling fluids : 80.1 [kg]
weight 3 drums empty : 6.8 [kg]
weight ammunition (1500 rounds) : 59.3 [kg]
weight signal pistol with cartridges : 3.6 [kg]
*******************************************************************
calculated operational weight empty : 2568 [kg] (70.8 [%])
published operational weight empty : 2400 [kg] (66.2 [%])
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weight crew : 243 [kg]
weight fuel for 2.0 hours flying : 196 [kg]
********************************************************************
operational weight : 3007 [kg](82.9 [%])
bomb load : 350 [kg]
operational weight bombing mission : 3357 [kg]
fuel reserve : 214 [kg] enough for 2.18 [hours] flying
possible additional useful load : 55 [kg]
operational weight fully loaded : 3626 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 3626 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 9.78 [kg/kW]
total power : 370.7 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.7 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.8 [g]
design flight time : 2.95 [hours]
design cycles : 492 sorties, design hours : 1450 [hours]
wing loading (MTOW) : 524 [N/m^2]
wing stress (3 g) during operation : 230 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.11 ["]
max.angle of attack (stalling angle) : 11.42 ["]
angle of attack at max.speed : 2.69 ["]
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 : 0.34 [ ]
induced drag coefficient at max.speed : 0.0066 [ ]
drag coefficient at max.speed : 0.0590 [ ]
drag coefficient (zero lift) : 0.0523 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 90 [km/u]
landing speed at sea-level (OW without bombload): 108 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 110 [km/hr] at 1996 [m] (power:46 [%])
min. power speed (max range) : 126 [km/hr] at 1996 [m] (power:52 [%])
max.rate of climb speed : 102.1 [km/hr] at sea-level
cruising speed : 148 [km/hr] op 1996 [m] (power:69 [%])
design speed prop : 157 [km/hr]
maximum speed : 165 [km/hr] op 100 [m] (power:100 [%])
climbing speed at sea-level (without bombload) : 232 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 261 [m]
lift/drag ratio : 9.15 [ ]
max. practical ceiling : 5550 [m] with flying weight :2635 [kg]
practical ceiling (operational weight): 4725 [m] with flying weight :3007 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 3650 [m] with flying weight :3528 [kg]
published ceiling (3993 [m]
climb to 1500m (without bombload) : 6.71 [min]
climb to 3000m (without bombload) : 16.40 [min]
max.dive speed : 446.3 [km/hr] at 2650 [m] height
load factor at max.angle turn 1.74 ["g"]
turn radius at 500m: 92 [m]
time needed for 360* turn 16.1 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 4.18 [hours] with 3 crew and 405 [kg] bombload
published endurance : 3.68 [hours] with 3 crew and possible useful (bomb) load :
454 [kg] and 88.1 [%] fuel
action radius : 603 [km] with 3 crew and 20[kg] photo camera/radio transmitter
max range theoretically with additional fuel tanks for total 1419 [litre] fuel : 1576
[km]
useful load with action-radius 250km : 710 [kg]
production : 105.45 [tonkm/hour]
oil and fuel consumption per tonkm : 1.01 [kg]
_
I_°°>/
°
Fuel tanks visible behind the pilot seat. And bombs stored besides the rear-gunner
literatuur : Jane's Fighting aircraft WWI
bomber 1914-1939
prakt. handb. vliegt. deel 1
bombers 1914-19
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 3.4.1
