Hansa-Brandenburg W.12
role : maritime patrol escort
first flight : operational : May 1917
country : Germany
design :
production : 145 aircraft
general information :
The W.12s (under the Naval designation C3MG) served on the Western Front, based at the Naval air bases at Ostend and Zeebrugge. The aircraft had some success, and one shot down the British airship C.27.
users : Kriegsmarine
crew : 2
armament : 1 synchronized 7.92 [mm] (0.312 in) Spandau LMG 08/15 machine-gun
and 1 movable 7.92 [mm] (0.312 in) Parabellum MG 14 machine-gun for the observer
engine : 1 Benz Bz.III liquid-cooled 6 -cylinder inline engine 150 [hp](110.3 KW)
or Mercedes D.III 160 hp engine
dimensions :
wingspan : 11.2 [m], length : 9.65 [m], height : 3.3[m]
wing area : 36.2 [m^2]
weights :
max.take-off weight : 1460 [kg]
empty weight operational : 997 [kg] bombload : 0 [kg]
performance :
maximum speed : 161 [km/hr] at sea-level
service ceiling : 3300 [m]
endurance : 3.5 [hours]
estimated action radius : 254 [km]
description :
1-bay two float biplane no tip floats
two spar upper and lower wing
engine, fuel and bombload in or attached to fuselage, landing gear attached to the wing
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.64 [ ]
diameter airscrew 2.80 [m]
angle of attack prop : 15.98 [ ]
reduction : 1.00 [ ]
airscrew revs : 1420 [r.p.m.]
pitch at Max speed 1.89 [m]
blade-tip speed at Vmax and max revs. : 213 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.62 [m]
calculated wing chord (rounded tips): 1.80 [m]
wing aspect ratio : 6.93 []
estimated gap : 1.56 [m]
gap/chord : 0.97 [ ]
seize (span*length*height) : 357 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.2 [kg/hr]
fuel consumption(cruise speed) : 33.0 [kg/hr] (45.0 [litre/hr]) at 71 [%] power
distance flown for 1 kg fuel : 4.39 [km/kg]
estimated total fuel capacity : 179 [litre] (131 [kg])
calculation : *3* (weight)
weight engine(s) dry : 278.0 [kg] = 2.52 [kg/KW]
weight 13 litre oil tank : 1.1 [kg]
oil tank filled with 0.8 litre oil : 0.7 [kg]
oil in engine 6 litre oil : 5.5 [kg]
fuel in engine 1 litre fuel : 0.6 [kg]
weight 19 litre gravity patrol tank(s) : 2.9 [kg]
weight radiator : 15.8 [kg]
weight exhaust pipes & fuel lines 10.2 [kg]
weight cowling 4.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 337 [kg](23.1 [%])
***************************************************************
fuselage skeleton (wood gauge : 8.13 [cm]): 144 [kg]
bracing : 8.6 [kg]
fuselage covering ( 13.6 [m2] doped linen fabric) : 4.4 [kg]
weight controls + indicators: 6.3 [kg]
Note the radiator on the top wing, does this belong to the Mercedes 160 hp engine? and is referred to as W. 12/V?
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 160 [litre] main fuel tank empty : 12.8 [kg]
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 192 [kg](13.2 [%])
***************************************************************
weight wing covering (doped linen fabric) : 23 [kg]
total weight ribs (74 ribs) : 87 [kg]
load on front upper spar (clmax) per running metre : 1267.9 [N]
load on rear upper spar (vmax) per running metre : 367.9 [N]
total weight 8 spars : 77 [kg]
weight wings : 187 [kg]
weight wing/square meter : 5.16 [kg]
Late production, Mercedes D.IIIa powered, Hansa-Brandenburg floatplanes
weight 4 interplane struts & cabane : 17.6 [kg]
weight cables (54 [m]) : 7.6 [kg] (= 139 [gram] per metre)
diameter cable : 4.8 [mm]
weight fin & rudder (1.8 [m2]) : 9.7 [kg]
weight stabilizer & elevator (4.1 [m2]): 21.3 [kg]
total weight wing surfaces & bracing : 243 [kg] (16.6 [%])
*******************************************************************
weight machine-gun(s) : 26.5 [kg]
weight pivot mounting mg :6.9 [kg]
weight ammunition magazine(s) :2.3 [kg]
weight Fokker Stangensteuerung synchronization gear : 1.0 [kg]
weight armament : 37 [kg]
********************************************************************
weight floats : 136 [kg] (9.3 [%])
*******************************************************************
********************************************************************
calculated empty weight : 945 [kg](64.7 [%])
weight oil for 4.2 hours flying : 9.3 [kg]
weight cooling fluids : 23.8 [kg]
weight 1 drums empty : 2.3 [kg]
weight ammunition (1000 rounds) : 30.5 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 1013 [kg] (69.4 [%])
published operational weight empty : 997 [kg] (68.3 [%])
_____________
| o |
-------------
= =
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 66 [kg]
********************************************************************
1395 at Zeebrugge
operational weight : 1241 [kg](85.0 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 1291 [kg]
fuel reserve : 65 [kg] enough for 1.97 [hours] flying
possible additional useful load : 104 [kg]
operational weight fully loaded : 1460 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1460 [kg] (100.0 [%])
||
I||==|
||
calculation : * 4 * (engine power)
power loading (operational without bombload) : 11.25 [kg/kW]
total power : 110.3 [kW] at 1420 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.4 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.6 [g]
design flight time : 2.80 [hours]
design cycles : 482 sorties, design hours : 1350 [hours]
operational wing loading : 336 [N/m^2]
wing stress (3 g) during operation : 195 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
In April 1918, a W.12 made an emergency landing in the neutral territory of the Netherlands, where it was interned and flight tested by the Dutch. In 1919 the government of the Netherlands bought a licence to build the aircraft. 35 W.12s were subsequently manufactured by the Van Berkel company of Rotterdam as the W-A, serving with the Dutch Naval Air Service (MLD) until 1933.
angle of attack zero lift : -1.21 ["]
max. angle of attack (stalling angle) : 12.67 ["]
angle of attack at max. speed : 2.15 ["]
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 : 0.28 [ ]
induced drag coefficient at max. speed : 0.0063 [ ]
drag coefficient at max. speed : 0.0351 [ ]
drag coefficient (zero lift) : 0.0289 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 79 [km/u]
landing speed at sea-level (OW without bombload): 95 [km/hr]
min. drag speed (max endurance) : 119 [km/hr] at 1650 [m](power :58 [%])
min. power speed (max range) : 125 [km/hr] at 1650 [m] (power:61 [%])
max. rate of climb speed : 105.6 [km/hr] at sea-level
cruising speed : 145 [km/hr] op 1650 [m] (power:74 [%])
design speed prop : 153 [km/hr]
maximum speed : 161 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 141 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 304 [m]
lift/drag ratio : 10.30 [ ]
max. practical ceiling : 3650 [m] with flying weight :1075 [kg]
practical ceiling (operational weight): 2725 [m] with flying weight :1241 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 1775 [m] with flying weight :1427 [kg]
published ceiling (3300 [m]
climb to 1500m (without bombload) : 12.74 [min]
max. dive speed : 394.8 [km/hr] at 775 [m] height
load factor at max. angle turn 1.46 ["g"]
turn radius at 500m: 70 [m]
time needed for 360* turn 16.3 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 3.97 [hours] with 2 crew and 154 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 3.50 [hours] with 2 crew and possible useful (bomb) load : 169 [kg] and 88.1 [%] fuel
action radius : 581 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 547 [litre] fuel : 1761 [km]
useful load with action-radius 250km : 287 [kg]
production : 41.62 [tonkm/hour]
oil and fuel consumption per tonkm : 0.85 [kg]
_
I_°°=/
====
Literature :
praktisch handboek vliegtuigen deel 1 page 279
Jane’s fighting aircraft WWI page 166f
Fighters 1914-19 page 93
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 29 Oktober 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4