AIRCRAFT INVESTIGATION
weight and performance calculations for the A.G.O.C.II
The C.II had the radiators below the upper wing centre-section
A.G.O.C.II
role : two-seat armed reconnaissance and artillery observation
importance : ***
first flight : operational : December 1915
country : Germany
design : August Haefeli
production : unknown, at Johannisthal, Berlin
general information :
This 2-seat reconnaissance biplane , built by the Aerowerke Gustav
Otto, had rather striking tail booms made of lightweight wood. Despite his
unusual construction it was a good airplane. It was fast and manoeuvrable and had an exceptional flight range. It remained active at the front until the end of 1916.
users : Germany
crew : 2
armament : 1 movable 7.92 [mm] (0.312 in) Parabellum MG 14 machine-gun for the
observer
engine : 1 Benz Bz.IV liquid-cooled 6 -cylinder inline engine 220 [hp](161.8 KW)
dimensions :
wingspan : 14.48 [m], length : 9.84 [m], height : 3.18[m]
wing area : 47.4 [m^2]
weights :
max.take-off weight : 1520 [kg]
empty weight operational : 0 [kg] bombload : 50 [kg]
performance :
maximum speed : 135 [km/hr] at sea-level
service ceiling : 4500 [m]
estimated action radius : 290 [km]
description :
3-bay biplane with fixed landing gear with nosewheel and tail strut
two spar upper and lower wing
tail supported by two fabric/plywood covered tail booms
engines, landing gear, fuel and bombs in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed pusher airscrew with max. efficiency :0.63 [ ]
estimated diameter airscrew 2.71 [m]
angle of attack prop : 14.13 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 1.61 [m]
blade-tip speed at Vmax and max revs. : 202 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.64 [m]
calculated wing chord (rounded tips): 1.79 [m]
wing aspect ratio : 8.85 []
estimated gap : 1.58 [m]
gap/chord : 0.97 [ ]
seize (span*length*height) : 453 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.1 [kg/hr]
fuel consumption(cruise speed) : 37.1 [kg/hr] (50.7 [litre/hr]) at 66 [%] power
distance flown for 1 kg fuel : 3.27 [km/kg]
estimated total fuel capacity : 274 [litre] (201 [kg])
calculation : *3* (weight)
weight engine(s) dry : 370.0 [kg] = 2.29 [kg/KW]
weight 17 litre oil tank : 1.5 [kg]
oil tank filled with 1.2 litre oil : 1.1 [kg]
oil in engine 9 litre oil : 8.1 [kg]
fuel in engine 1 litre fuel : 0.8 [kg]
weight 22 litre gravity patrol tank(s) : 3.2 [kg]
weight radiator : 24.3 [kg]
weight exhaust pipes & fuel lines 14.7 [kg]
weight self-starter : 4.0 [kg]
weight cowling 6.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 24.3 [kg]
total weight propulsion system : 457 [kg](30.1 [%])
***************************************************************
tail boom plywood covering (monocoque) : 51 [kg]
fuselage skeleton (wood gauge : 3.88 [cm]): 77 [kg]
houtdikte wordt erg dun !!!!!
houtdikte wordt erg dun !!!!!
als vliegtuig een canard heeft kan skelet relatief dun zijn
bracing : 5.4 [kg]
fuselage covering ( 25.6 [m2] doped linen fabric) : 8.2 [kg]
plywood covering : 51 [kg]
weight controls + indicators: 7.0 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 3.5 [kg]
weight 253 [litre] main fuel tank empty : 20.2 [kg]
weight engine mounts & firewalls : 8 [kg]
total weight fuselage : 192 [kg](12.6 [%])
***************************************************************
weight wing covering (doped linen fabric) : 30 [kg]
total weight ribs (76 ribs) : 90 [kg]
load on front upper spar (clmax) per running metre : 821.4 [N]
load on rear upper spar (vmax) per running metre : 289.5 [N]
total weight 8 spars : 99 [kg]
weight wings : 219 [kg]
weight wing/square meter : 4.63 [kg]
weight 12 interplane struts & cabane : 25.2 [kg]
weight cables (93 [m]) : 14.5 [kg] (= 155 [gram] per metre)
diameter cable : 5.0 [mm]
weight fin & rudder (2.4 [m2]) : 11.6 [kg]
weight stabilizer & elevator (4.5 [m2]): 21.3 [kg]
total weight wing surfaces & bracing : 292 [kg] (19.2 [%])
*******************************************************************
weight machine-gun(s) : 9.5 [kg]
weight Schneider ring mounting mg :5.5 [kg]
weight armament : 15 [kg]
********************************************************************
wheel pressure : 668.8 [kg]
weight 4 wheels (830 [mm] by 128 [mm]) : 61.8 [kg]
weight tailskid : 1.8 [kg]
weight undercarriage with axle 22.1 [kg]
total weight landing gear : 85.7 [kg] (5.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 1042 [kg](68.5 [%])
weight oil for 5.7 hours flying : 12.0 [kg]
weight cooling fluids : 35.0 [kg]
weight 1 drums empty : 2.3 [kg]
weight ammunition (500 rounds) : 16.4 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 1106 [kg] (72.8 [%])
estimated operational weight empty : 1057 [kg] (69.6 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 74 [kg]
********************************************************************
operational weight : 1342 [kg](88.3 [%])
bomb load : 50 [kg]
operational weight bombing mission : 1392 [kg]
weight camera : 20 [kg]
operational weight photo mission : 1362 [kg]
fuel reserve : 127 [kg] enough for 3.42 [hours] flying
possible additional useful load : 31 [kg]
operational weight fully loaded : 1520 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1520 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 8.30 [kg/kW]
total power : 161.8 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.0 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.1 [g]
design flight time : 3.34 [hours]
design cycles : 299 sorties, design hours : 1000 [hours]
operational wing loading : 282 [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 : -1.14 ["]
max. angle of attack (stalling angle) : 11.88 ["]
angle of attack at max. speed : 2.57 ["]
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 : 0.33 [ ]
induced drag coefficient at max. speed : 0.0068 [ ]
drag coefficient at max. speed : 0.0660 [ ]
drag coefficient (zero lift) : 0.0592 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 72 [km/u]
landing speed at sea-level (OW without bombload): 86 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 88 [km/hr] at 2250 [m] (power:43 [%])
min. power speed (max range) : 102 [km/hr] at 2250 [m] (power:49 [%])
max. rate of climb speed : 82.9 [km/hr] at sea-level
cruising speed : 122 [km/hr] op 2250 [m] (power:66 [%])
design speed prop : 128 [km/hr]
maximum speed : 135 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 234 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 139 [m]
lift/drag ratio : 8.12 [ ]
max. practical ceiling : 5125 [m] with flying weight :1188 [kg]
practical ceiling (operational weight): 4425 [m] with flying weight :1342 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 3825 [m] with flying weight :1483 [kg]
published ceiling (4500 [m]
climb to 1500m (without bombload) : 7.23 [min]
climb to 3000m (without bombload) : 18.35 [min]
max. dive speed : 322.9 [km/hr] at 2825 [m] height
load factor at max. angle turn 1.92 ["g"]
turn radius at 500m: 51 [m]
time needed for 360* turn 11.1 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 5.42 [hours] with 2 crew and 51 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 4.77 [hours] with 2 crew and possible useful (bomb) load : 75 [kg] and 88.1 [%] fuel
action radius : 379 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 491 [litre] fuel : 1178 [km]
useful load with action-radius 250km : 207 [kg]
production : 25.16 [tonkm/hour]
oil and fuel consumption per tonkm : 1.56 [kg]
_
°°_I>-/
°°
No radiators beside the fuselage, radiator is below upper wing centre-section > is a C.II
Literature :
Praktisch handboek vliegtuigen deel 1 page 251
Bombers 1914-19 page 18
Jane’s fighter aircraft WOI page 136
German aircraft of the first world war page 247
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/
content please mail to below mail address
(c) B van der Zalm 23 November 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4