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weight and performance calculations for the Hansa-Brandenburg W.19
Hansa-Brandenburg W.19
importance : ***
first flight : operational : January 1918
country : Germany
design :
production : 55 aircraft
general information :
Bigger version of the W.12 giving greater range and endurance. In operation the W.19
would fly ahead on reconnaissance missions, while the W.12 colleagues waited on the
surface for their signal if anything was spotted. On 4 June 1918 a hot fight took place
near Terschelling between 4 Felixtowe flying boats, commanded by capt.Leckie and 15
assorted W.12, W.19 and W.29 German floatplanes. 2 German floatplanes were
shot down, one F2a flying boat was interned by a Dutch trawler and one F2a was about
of beaching at Terschelling island when it was shot on fire.
users : Germany
crew : 2
armament : 2 synchronized 7.92 [mm] (0.312 in) Spandau LMG 08/15 machine-guns
and 1 movable 7.92 [mm] (0.312 in) Parabellum MG 14 machine-gun for the observer
engine : 1 Maybach IVa liquid-cooled 6 -cylinder inline engine 245 [hp](182.7 KW)
dimensions :
wingspan : 13.8 [m], length : 10.65 [m], height : 4.1[m]
wing area : 57.8 [m^2]
weights :
max.take-off weight : 2005 [kg]
empty weight operational : 1435 [kg] bombload : 0 [kg]
performance :
maximum speed : 151 [km/hr] at sea-level
service ceiling : 4500 [m]
endurance : 5.0 [hours]
estimated action radius : 340 [km]
description :
2-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 [ ]
estimated diameter airscrew 3.14 [m]
angle of attack prop : 13.66 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 1.80 [m]
blade-tip speed at Vmax and max revs. : 234 [m/s]
calculation : *1* (dimensions)
mean wing chord : 2.09 [m]
calculated wing chord (rounded tips): 2.33 [m]
wing aspect ratio : 6.59 []
estimated gap : 1.73 [m]
gap/chord : 0.83 [ ]
seize (span*length*height) : 603 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.8 [kg/hr]
fuel consumption(cruise speed) : 47.3 [kg/hr] (64.5 [litre/hr]) at 85 [%] power
distance flown for 1 kg fuel : 2.87 [km/kg]
estimated total fuel capacity : 366 [litre] (268 [kg])
calculation : *3* (weight)
weight engine(s) dry : 400.0 [kg] = 2.19 [kg/KW]
weight 30 litre oil tank : 3.8 [kg]
oil tank filled with 1.4 litre oil : 1.2 [kg]
oil in engine 10 litre oil : 9.1 [kg]
fuel in engine 1 litre fuel : 0.9 [kg]
weight 27 litre gravity patrol tank(s) : 2.7 [kg]
weight radiator : 27.4 [kg]
weight exhaust pipes & fuel lines 18.8 [kg]
weight self-starter : 4.5 [kg]
weight cowling 7.3 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 27.4 [kg]
total weight propulsion system : 499 [kg](24.9 [%])
***************************************************************
fuselage skeleton (wood gauge : 9.18 [cm]): 202 [kg]
bracing : 13.4 [kg]
fuselage covering ( 16.6 [m2] doped linen fabric) : 5.3 [kg]
weight controls + indicators: 6.8 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight transceiver : 27 [kg]
weight 339 [litre] main fuel tank empty : 32.5 [kg]
weight engine mounts & firewalls : 9 [kg]
total weight fuselage : 307 [kg](15.3 [%])
***************************************************************
weight wing covering (doped linen fabric) : 37 [kg]
total weight ribs (78 ribs) : 119 [kg]
load on front upper spar (clmax) per running metre : 1213.1 [N]
load on rear upper spar (vmax) per running metre : 379.3 [N]
total weight 8 spars : 112 [kg]
weight wings : 268 [kg]
weight wing/square meter : 4.63 [kg]
weight 8 interplane struts & cabane : 33.2 [kg]
weight cables (80 [m]) : 16.3 [kg] (= 202 [gram] per metre)
diameter cable : 5.7 [mm]
weight fin & rudder (2.8 [m2]) : 13.2 [kg]
weight stabilizer & elevator (6.5 [m2]): 30.6 [kg]
total weight wing surfaces & bracing : 361 [kg] (18.0 [%])
*******************************************************************
weight machine-gun(s) : 43.5 [kg]
weight Schneider ring mounting mg :5.5 [kg]
weight ammunition magazine(s) :3.5 [kg]
weight Fokker Zentralsteuerung synchronization gear : 2.0 [kg]
weight armament : 55 [kg]
********************************************************************
weight floats : 164 [kg] (8.2 [%])
*******************************************************************
W.19 prototype
********************************************************************
calculated empty weight : 1386 [kg](69.1 [%])
weight oil for 6.0 hours flying : 23.0 [kg]
weight cooling fluids : 37.6 [kg]
weight 1 drums empty : 2.3 [kg]
weight ammunition (1500 rounds) : 44.6 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 1496 [kg] (74.6 [%])
published operational weight empty : 1435 [kg] (71.6 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 95 [kg]
********************************************************************
operational weight : 1752 [kg](87.4 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 1802 [kg]
fuel reserve : 174 [kg] enough for 3.68 [hours] flying
possible additional useful load : 29 [kg]
operational weight fully loaded : 2005 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 2005 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 9.59 [kg/kW]
total power : 182.7 [kW] at 1400 [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 : 2.4 [g]
design flight time : 3.50 [hours]
design cycles : 371 sorties, design hours : 1300 [hours]
operational wing loading : 297 [N/m^2]
wing stress (3 g) during operation : 193 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.23 ["]
max. angle of attack (stalling angle) : 12.80 ["]
angle of attack at max. speed : 2.20 ["]
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 : 0.28 [ ]
induced drag coefficient at max. speed : 0.0067 [ ]
drag coefficient at max. speed : 0.0450 [ ]
drag coefficient (zero lift) : 0.0384 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 74 [km/u]
landing speed at sea-level (OW without bombload): 89 [km/hr]
min. drag speed (max endurance) : 108 [km/hr] at 2250 [m](power :54 [%])
min. power speed (max range) : 117 [km/hr] at 2250 [m] (power:57 [%])
max. rate of climb speed : 96.4 [km/hr] at sea-level
cruising speed : 136 [km/hr] op 2250 [m] (power:71 [%])
design speed prop : 143 [km/hr]
maximum speed : 151 [km/hr] op 100 [m] (power:100 [%])
climbing speed at sea-level (without bombload) : 180 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 151 [m]
lift/drag ratio : 8.71 [ ]
max. practical ceiling : 6250 [m] with flying weight :1551 [kg]
practical ceiling (operational weight) : 5325 [m] with flying weight :1752 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 4450 [m] with flying weight :1958 [kg]
published ceiling (4500 [m]
climb to 1500m (operational weight without bombload) : 8.36 [min]
climb to 3000m (operational weight without bombload) : 17.51 [min]
max. dive speed : 394.4 [km/hr] at 3450 [m] height
load factor at max. angle turn 1.70 ["g"]
turn radius at 500m: 56 [m]
time needed for 360* turn 12.8 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 5.67 [hours] with 2 crew and 79 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 5.00 [hours] with 2 crew and possible useful (bomb) load : 111 [kg] and 88.1 [%] fuel
action radius : 470 [km] with 2 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 651 [litre] fuel : 1373 [km]
useful load with action-radius 250km : 304 [kg]
production : 41.26 [tonkm/hour]
oil and fuel consumption per tonkm : 1.24 [kg]
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Literature :
German aircraft of the first world war page 73
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/
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(c) B van der Zalm 31 May 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4