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weight and performance calculations for the Handley Page W8b
Handley Page W.8b (H.P.18)
role : passenger aircraft
importance : ***
first flight : 02 December 1919 operational : June 1921
country : United-Kingdom
design : Volkert assisted by S.T.A.Richards
production : 25 aircraft
general information :
The W.8 was the first British aircraft specially designed for passenger transport. In 1920 it was seen as the best passenger aircraft regarding safety, speed and comfort. The prototype G-EAPJ had 450hp Napier Lion engines. It set a record by bringing a payload of 1674kg to a height of 4267m. The W8b with less powerful Rolls Royce Eagle engines and seating for 12 passengers entered service in 1922 with the Handley Page Transport LTD, flying on the route London-Paris-Brussels. It remained in service well into the 1930’s. G-EBBI was in service for 10 years till October 1932 when it had flown for 800.000km in 5473 hrs (average 146 km/hr, 1.5 hrs a day). From the W.8 the W.9 and W.10 were developed in the 1920’s.
The gearing of the propellor with the Rolls Royce Eagle engine failed frequently.
Users : SABENA, Imperial airways, Handley Page Transport
registrations : G-EAPJ, C-5414, G-EBBH, G-EBBG, G-EBBI, G-EBLE,G-EBMT,G-EBMR, G-EBMM, G-EBMS
crew : 2 passengers : 12
engine : 2 Rolls Royce Eagle VIII liquid-cooled 12 -cylinder V-engine 360 [hp](268.5 KW)
dimensions :
wingspan : 22.26 [m], length : 18.31 [m], height : 5.18[m]
wing area : 135.3 [m^2]
weights :
max.take-off weight : 5436 [kg]
empty weight operational : 3490 [kg] useful load : 1200 [kg]
performance :
maximum speed :167 [km/hr] at sea-level
cruise speed :150 [km/u] op 100 [m]
service ceiling : 3280 [m]
range : 805 [km]
description :
3-bay biplane with fixed underwing 4 -wheel landing gear and tail strut
two spar upper and lower wing
engines, landing gear and fuel attached to the wings, useful load in the fuselage
airscrew :
two fixed pitch 4 -bladed tractor airscrews with max. efficiency :0.59 [ ]
estimated diameter airscrew 3.19 [m]
angle of attack prop : 18.36 [ ]
reduction : 0.62 [ ]
airscrew revs : 1116 [r.p.m.]
pitch at Max speed 2.49 [m]
blade-tip speed at Vmax and max revs. : 192 [m/s]
calculation : *1* (dimensions)
wing chord : 3.05 [m]
mean wing chord : 3.04 [m]
calculated wing chord (rounded leading edge tips): 3.11 [m]
wing aspect ratio : 7.32 []
gap : 3.35 [m]
gap/chord : 1.10 [ ]
seize (span*length*height) : 2111 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 9.7 [kg/hr]
fuel consumption(cruise speed) : 122.7 [kg/hr] (167.4 [litre/hr]) at 68 [%] power
distance flown for 1 kg fuel : 1.22 [km/kg] at 1640 [m] cruise height, sfc : 338.1 [kg/kwh]
estimated total fuel capacity : 1017.62 [litre] (745.92 [kg])
calculation : *3* (weight)
weight engine(s) dry : 758.0 [kg] = 1.41 [kg/KW]
weight reduction gear : 59.1 [kg]
weight 82.6 litre oil tank : 7.02 [kg]
oil tank filled with 4.0 litre oil : 3.6 [kg]
oil in engine 29.9 litre oil : 26.8 [kg]
fuel in engine 3.7 litre fuel : 2.68 [kg]
weight 71.2 litre gravity patrol tank(s) : 10.7 [kg]
weight radiator : 85.9 [kg]
weight exhaust pipes & fuel lines 36.4 [kg]
weight self-starter : 6.6 [kg]
weight cowling 10.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 101.9 [kg]
total weight propulsion system : 1161 [kg](21.4 [%])
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fuselage skeleton (wood gauge : 10.91 [cm]): 558 [kg]
fuselage width : 1.52 [m]
cabin layout : pitch : 87 [cm] (1+1) seating in 6.0 rows
passenger cabin area : 7.36 [m2]
weight 12.0 windows : 10.80 [kg]
passenger cabin width : 1.41 [m] cabin length : 5.22 [m] cabin height : 1.90 [m]
cabin space : 13.99 [m3]
weight cabin furbishing : 70.55 [kg]
bracing : 77.4 [kg]
fuselage covering ( 63.3 [m2] doped linen fabric) : 19.6 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 8.8 [kg]
weight seats : 70.0 [kg]
weight air conditioning : 18 [kg]
total weight fuselage : 836 [kg](15.4 [%])
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weight wing covering (doped linen fabric) : 107 [kg]
total weight ribs (146 ribs) : 323 [kg]
weight engine mounts : 27 [kg]
weight two 473 [litre] main fuel tanks empty : 75.7 [kg]
load on front upper spar (clmax) per running metre : 913.4 [N]
load on rear upper spar (vmax) per running metre : 566.3 [N]
total weight 8 spars : 155 [kg]
weight wings : 586 [kg]
weight wing/square meter : 4.33 [kg]
weight 12 interplane struts & cabane : 313.8 [kg]
weight cables (169 [m]) : 41.3 [kg] (= 245 [gram] per metre)
diameter cable : 6.3 [mm]
weight fin & rudder (5.8 [m2]) : 25.8 [kg]
weight stabilizer & elevator (15.2 [m2]): 66.9 [kg]
total weight wing surfaces & bracing : 1136 [kg] (20.9 [%])
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wheel pressure : 1359.0 [kg]
weight 4 wheels (870 [mm] by 134 [mm]) : 93.5 [kg]
weight tailskid : 13.9 [kg]
weight undercarriage with axle 148.3 [kg]
total weight landing gear : 255.7 [kg] (4.7 [%]
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calculated empty weight : 3390 [kg](62.4 [%])
weight oil for 6.4 hours flying : 62.1 [kg]
weight cooling fluids : 116.0 [kg]
calculated operational weight empty : 3568 [kg] (65.6 [%])
published operational weight empty : 3490 [kg] (64.2 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 245 [kg]
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operational weight empty: 3975 [kg](73.1 [%])
weight 12 passengers : 924 [kg]
weight luggage & freight : 276 [kg]
operational weight loaded: 5175 [kg](73.1 [%])
fuel reserve : 260.7 [kg] enough for 2.12 [hours] flying
operational weight fully loaded : 5436 [kg] with fuel tank filled for 68 [%]
published maximum take-off weight : 5436 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 10.12 [kg/kW]
power loading (operational without useful load) : 7.40 [kg/kW]
total power : 536.9 [kW] at 1800 [r.p.m]
W.8e with additional engine in the nose to reduce the risks involved with engine failure
calculation : *5* (loads)
manoeuvre load : 3.0 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]
design flight time : 3.75 [hours]
design cycles : 822 sorties, design hours : 3080 [hours]
operational wing loading : 288 [N/m^2]
wing stress (3 g) during operation : 200 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.43 ["]
max. angle of attack (stalling angle) : 12.27 ["]
angle of attack at max. speed : 1.20 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.12 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max. speed : 0.22 [ ]
induced drag coefficient at max. speed : 0.0038 [ ]
drag coefficient at max. speed : 0.0376 [ ]
drag coefficient (zero lift) : 0.0339 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 73 [km/u]
stalling speed at sea-level (MTOW): 85 [km/u]
landing speed at sea-level: 86 [km/hr]
min. drag speed (max endurance) : 104 [km/hr] at 1640 [m](power :42 [%])
min. power speed (max range) : 112 [km/hr] at 1640 [m] (power:44 [%])
max. rate of climb speed : 102.4 [km/hr] at sea-level
cruising speed : 150 [km/hr] op 1640 [m] (power:68 [%])
design speed prop : 159 [km/hr]
maximum speed : 167 [km/hr] op 100 [m] (power:98 [%])
climbing speed at sea-level : 247 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 102.3 [km/u]
static prop wash : 128 [km/u]
take-off distance at sea-level : 188 [m]
lift/drag ratio : 9.78 [ ]
climb to 1000m with max payload : 10.42 [min]
climb to 1500m with max payload : 19.14 [min]
climb to 2000m with max payload : 34.06 [min]
published ceiling (3280 [m]
practical ceiling (operational weight) : 4043 [m] with flying weight :3975 [kg] line 3385
practical ceiling fully loaded (mtow-30 min.fuel) : 2628 [m] with flying weight :5375 [kg]
calculation *10* (action radius & endurance)
published range : 805 [km] with 2 crew and 1048.9 [kg] useful load and 88.1 [%] fuel
range : 620 [km] with 2 crew and 1200.0 [kg] useful load and 67.9 [%] fuel
max range theoretically with additional fuel tanks for total 2438.1 [litre] fuel : 2189.1 [km]
useful load with range 500km : 1379 [kg]
production : 207.26 [tonkm/hour]
oil and fuel consumption per tonkm : 0.64 [kg]
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Literature :
Handley Page W/8 / H.P.18 (flyingmachines.ru)
Wikipedia
Praktisch handbook vliegtuigen deel 2 page 70,71
Piston-engined airliners page 4
ELTA (geschiedenis-van-amsterdam-noord.nl)
The W8b (Reg C-5414) was the biggest aircraft demonstrating at the ELTA held in August 1919 in Amsterdam. Upon landing the wheels sank in the soft ground at the field in Amsterdam-North (Papaverweg) (now Volewijck) were the ELTA was held resulting in a nose-stand.
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 01 January 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4