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weight and performance calculations for the Handley-Page O/100
Handley-Page O/100
role : heavy bomber
importance : ***
first flight : 18 December 1915 operational : November 1916
country : United-Kingdom
design : Handley Page & George Volkert
production : 42 aircraft
general information :
December 1914 the Air Department of the Admirality sent out a requirement ( by Commodore Murray F. Sueter) for a “Bloody paralyser of an aeroplane” for the bombing of Germany. The first bomber s/n 1455 made the first flight on 18 December 1915. Flight trials took place at Eastchurch beginning January 1916. The first O/100 went into service with No.3 wing RNAS on the western front in December 1916. At first they were used for daylight sea patrols of the Flanders coast, but from march 1917 they started with night bombing of major German installations, like U-boat bases, railway stations and industrial targets.
The streamlined nacelles for the engines also housed the main fuel tanks.
Design based on RR Eagle engine which at that moment was still under development.
Fuel & oil : 1284 kg crew : 345 kg bombload : 907 kg
An experimental version with 4 Hispano Suiza 200 hp engines existed.
Fuel capacity : 300 gallon = 1364 litre (ca.996 kg), endurance : 8 hrs. The O/100 was the first heavy bomber after the Russian Sikorsky Ilya Murometz bomber. It was much bigger then the German Gotha G.IV and G.V medium weight bombers
users : RFC
crew : 4
armament : 4 movable 7.70 [mm] (0.303 in) Lewis machine-guns
engine : 2 Rolls Royce Eagle II liquid-cooled 12 -cylinder V-engine 250 [hp](183.9 KW)
dimensions :
wingspan : 30.48 [m], length : 19.15 [m], height : 6.71[m]
wing area : 153.1 [m^2]
weights :
max.take-off weight : 6352 [kg]
empty weight operational : 3630 [kg] bombload : 700 [kg]
performance :
maximum speed : 153 [km/hr] at sea-level
service ceiling : 2134 [m]
endurance : 8.165 [hours]
estimated action radius : 562 [km]
description :
3-bay biplane with fixed underwing 4 -wheel landing gear and tail strut
upper wingtips supported by slanted flying wires
two spar upper and lower wing
engines, landing gear and fuel attached to the wings, bombload in or attached to fuselage
wings can be folded for easy storage
airscrew :
two fixed pitch 4 -bladed tractor airscrews with max. efficiency :0.60 [ ]
estimated diameter airscrew 3.59 [m]
angle of attack prop : 10.67 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1600 [r.p.m.]
pitch at Max speed 1.59 [m]
blade-tip speed at Vmax and max revs. : 304 [m/s]
calculation : *1* (dimensions)
mean wing chord : 2.79 [m]
calculated wing chord (rounded tips): 2.98 [m]
wing aspect ratio : 10.92 []
estimated gap : 3.10 [m]
gap/chord : 1.11 [ ]
seize (span*length*height) : 3917 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 5.5 [kg/hr]
fuel consumption(cruise speed) : 107.9 [kg/hr] (147.2 [litre/hr]) at 76 [%] power
distance flown for 1 kg fuel : 1.28 [km/kg]
estimated total fuel capacity : 1364 [litre] (1000 [kg])
calculation : *3* (weight)
weight engine(s) dry : 758.0 [kg] = 2.06 [kg/KW]
weight 69 litre oil tank : 8.7 [kg]
oil tank filled with 2.8 litre oil : 2.5 [kg]
oil in engine 20 litre oil : 18.4 [kg]
fuel in engine 3 litre fuel : 1.8 [kg]
weight 63 litre gravity patrol tank(s) : 6.1 [kg]
weight radiator : 58.8 [kg]
weight exhaust pipes & fuel lines 28.9 [kg]
weight self-starter : 4.5 [kg]
weight cowling 7.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 69.9 [kg]
total weight propulsion system : 956 [kg](15.1 [%])
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fuselage skeleton (wood gauge : 11.29 [cm]): 625 [kg]
bracing : 90.8 [kg]
fuselage covering ( 69.3 [m2] doped linen fabric) : 22.2 [kg]
O/100 captured by the Germans
weight controls + indicators: 11.5 [kg]
weight seats : 12.0 [kg]
weight other details, lighting set, etc. : 9.1 [kg]
weight bomb storage : 49.0 [kg]
weight interior + equipment + fuel lines: 68 [kg]
weight 1 fire extinguisher : 3 [kg]
total weight fuselage : 891 [kg](14.0 [%])
***************************************************************
weight wing covering (doped linen fabric) : 98 [kg]
total weight ribs (186 ribs) : 378 [kg]
weight engine mounts : 18 [kg]
weight two 651 [litre] main fuel tanks empty : 124.9 [kg]
load on front upper spar (clmax) per running metre : 720.7 [N]
load on rear upper spar (vmax) per running metre : 487.1 [N]
total weight 8 spars : 253 [kg]
weight wings : 728 [kg]
weight wing/square meter : 4.76 [kg]
weight wing folding system : 55 [kg]
weight 12 interplane struts & cabane : 258.4 [kg]
weight cables (163 [m]) : 64.8 [kg] (= 398 [gram] per metre)
diameter cable : 8.1 [mm]
weight fin & rudder (10.8 [m2]) : 52.9 [kg]
weight stabilizer & elevator (17.2 [m2]): 83.1 [kg]
total weight wing surfaces & bracing : 1385 [kg] (21.8 [%])
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weight machine-gun(s) : 50.8 [kg]
weight Scarff ring mounting mg :27.7 [kg]
weight armament : 78 [kg]
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wheel pressure : 1588.0 [kg]
weight 4 wheels (870 [mm] by 134 [mm]) : 113.0 [kg]
weight tailskid : 8.1 [kg]
weight undercarriage with axle 150.4 [kg]
total weight landing gear : 271.4 [kg] (4.3 [%]
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calculated empty weight : 3583 [kg](56.4 [%])
weight oil for 9.8 hours flying : 54.0 [kg]
weight cooling fluids : 75.8 [kg]
weight 20 drums empty : 4.1 [kg]
weight ammunition (940 rounds) : 29.9 [kg]
weight Very pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 3747 [kg] (59.0 [%])
published operational weight empty : 3630 [kg] (57.1 [%])
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weight crew : 324 [kg]
weight fuel for 2.0 hours flying : 216 [kg]
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operational weight : 4287 [kg](67.5 [%])
bomb load : 700 [kg]
operational weight bombing mission : 4987 [kg]
fuel reserve : 784 [kg] enough for 7.27 [hours] flying operational weight fully loaded : 6352 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 6352 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 17.27 [kg/kW]
total power : 367.8 [kW] at 1600 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.1 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]
design flight time : 5.72 [hours]
Fuselage skeleton
design cycles : 140 sorties, design hours : 800 [hours]
wing loading (MTOW) : 407 [N/m^2]
wing stress (3 g) during operation : 201 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.31 ["]
max. angle of attack (stalling angle) : 10.77 ["]
angle of attack at max. speed : 1.43 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.12 [ ]
lift coefficient at max. angle of attack : 1.10 [ ]
lift coefficient at max. speed : 0.25 [ ]
induced drag coefficient at max. speed : 0.0024 [ ]
drag coefficient at max. speed : 0.0303 [ ]
drag coefficient (zero lift) : 0.0278 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 73 [km/u]
landing speed at sea-level (OW without bombload): 87 [km/hr]
min. drag speed (max endurance) : 87 [km/hr] at 1067 [m](power :36 [%])
min. power speed (max range) : 99 [km/hr] at 1067 [m] (power:40 [%])
max. rate of climb speed : 92.0 [km/hr] at sea-level
cruising speed : 138 [km/hr] op 1067 [m] (power:70 [%])
Handley Page 0/100,serial 3119 of RAF No. 214 Sqn. After an emergency landing near Ritthem April 12, 1918 and caught fire. Crew: fl.cdr. E.R. Barker, obs.lt. F.H. Hudson, fl.sub.lt. D.C. Kimmond. [at Beeldbank NIMH]
design speed prop : 145 [km/hr]
maximum speed : 153 [km/hr] op 100 [m] (power:98 [%])
climbing speed at sea-level (without bombload) : 168 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 163 [m]
lift/drag ratio : 15.21 [ ]
max. practical ceiling : 4400 [m] with flying weight :3847 [kg]
practical ceiling (operational weight) : 3900 [m] with flying weight :4287 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 1925 [m] with flying weight :6244 [kg]
published ceiling (2134 [m]
climb to 1500m (without bombload) : 10.17 [min]
max. dive speed : 378.9 [km/hr] at 925 [m] height
load factor at max. angle turn 1.88 ["g"]
turn radius at 500m: 60 [m]
time needed for 360* turn 12.3 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 9.27 [hours] with 4 crew and 1281 [kg] bombload and 100.0 [%] fuel
published endurance : 8.16 [hours] with 4 crew and possible useful (bomb) load : 1400 [kg] and 88.1 [%] fuel
action radius : 1443 [km] with 4 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 3491 [litre] fuel : 3266 [km]
useful load with action-radius 250km : 1889 [kg]
production : 260.16 [tonkm/hour]
oil and fuel consumption per tonkm : 0.44 [kg]
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I_°°>/
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Crashed O/100
Literature :
Praktisch handboek vliegtuigen deel 1 page 185
Bombers 1914-19 page 153
Wikipedia
Warplanes WOI page 62,75,132,134fd
Jane’s FAWOI page 72
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 09 February 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4