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weight and performance calculations for the Handley Page H.P.42W (H.P.45)
Handley Page H.P.42W (H.P.45)
role : multi-engined passenger aircraft
importance : **
first flight : 14 November 1930 “Hannibal” flown by sq.lr Thomas Harold England operational : August 1931
country : United-Kingdom
design : G.R.Volkert and H.D.Boultbee
nickname : “Flying Banana”
production : 4 H.P.42E and 4 H.P.42W aircraft at Radlett, Herfordshire
general information :
Replacement for the DH66 and Argosy. It used the same design filosophy, with emphasize on safety, regularity and comfort above speed. Biggest airliner in use in 1931. It was developed in two versions :
H.P.42 > for the Eastern routes pax 18-24 (H.P.42E), less passenger with greater range (800km) 490 hp Jupiter XIF engines, with provisions to carry a useful load of mail. They were stationed in Cairo.
H.P.45 > for the European routes pax 38 (H.P.42W), more passengers over a smaller range (480 km) Jupiter XFBM engines
Airfoil : RAF 28. Fuel capacity : 2273 litres.
The large wing area gave a low wingloading for low landingspeed. Capable to land on grass or unpaved runways. The low lingloading made the aircraft more wallow about in turbulent air.
Reliable aircraft, popular with its passengers and operator, that was kept in service upon WWII and then it was used by the military as troop transport. The rugged construction made it possible to operate in remote areas without problems. The luxureous passenger cabin with good soundproofing and first-class catering made travelling with the H.P.42 a nice experience.
The 8 aircraft flew in total 16.093.000 km, each aircraft amassing more then 12.000 flying hours. No passenger was ever killed flying with the HP42 during its civil career.
Heracles had carried 95.000 passengers on 01 september 1938 after 7 years in service flying nearly 1 million kilometres. (2500 flights with 38 pax = 95.000 km, distance 400 km for each flight > 1 mln km)
The top wing had automatic slots.
users : Imperial Airways
crew : 4 passengers : 38
registrations : HP42E : G-AAGX Hannibal, G-AAUC Horsa, G-AAUD Hanno, G-AAUE Hadrian HP42W G-AAXC Heracles, G-AAXD Horatius, G-AAXE Hengist, G-AAXF Helena
engine : 4 Bristol Jupiter XFBM air-cooled 9 -cylinder radial engine 555 [hp](413.9 KW)
supercharged engine, critical height : 1219 [m]
dimensions :
wingspan : 39.62 [m], length : 27.36 [m], height : 8.02[m]
wing area : 277.7 [m^2]
weights :
max.take-off weight : 13380 [kg]
empty weight operational : 8047 [kg] useful load : 3800 [kg]
performance :
maximum speed :204 [km/hr] at sea-level
cruise speed :184 [km/u] op 100 [m]
service ceiling : 4000 [m]
range : 800 [km]
description :
2½-bay sesquiplane with fixed landing gear and tail wheel
upper wingtips supported by slanted struts
two spar upper and lower wing
construction : Aluminium wing structure covered with fabric. Fuselage forward 2/3
monocoque construction of corrugated aluminium. Rear 1/3 fuselage steel tubes
covered with fabric. Engines clustered as close together as possible.
engines, landing gear and fuel attached to the wings, useful load in the fuselage
airscrew :
four wooden fixed pitch 4 -bladed tractor airscrews with max. efficiency :0.62 [ ]
estimated diameter airscrew 3.58 [m]
power loading prop : 57.80 [KW/m]
prop efficiency ratio: 3.08 [1/s]
angle of attack prop : 20.13 [ ]
reduction : 0.50 [ ]
airscrew revs : 1100 [r.p.m.]
pitch at Max speed 3.09 [m]
blade-tip speed at Vmax and max revs. : 214 [m/s]
calculation : *1* (dimensions)
measured wing chord : 4.86 [m] at 50% wingspan
mean wing chord : 4.67 [m]
wing aspect ratio : 8.48 []
estimated gap : 3.51 [m]
gap/chord : 0.75 [ ]
seize (span*length*height) : 8694 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 41.4 [kg/hr]
fuel consumption(cruise speed) : 408.4 [kg/hr] (557.1 [litre/hr]) at 81 [%] power
distance flown for 1 kg fuel : 0.45 [km/kg] at 2000 [m] height, sfc : 303.9 [kg/kwh]
estimated total fuel capacity : 2273 [litre] (1666 [kg])
calculation : *3* (weight)
weight engine(s) dry : 1852.0 [kg] = 1.12 [kg/KW]
weight reduction gear : 82.8 [kg]
weight 240.3 litre oil tank : 20.42 [kg]
oil tank filled with 12.4 litre oil : 11.1 [kg]
oil in engine 9.2 litre oil : 8.3 [kg]
fuel in engine 11.3 litre fuel : 8.28 [kg]
weight 236.9 litre gravity patrol tank(s) : 35.5 [kg]
Refuelling of H.P.42 Hanno at Samakh, Tiberias, Palestine in October 1931
weight Bristol type gas starter : 10.1 [kg]
weight cowling 16.6 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 355.0 [kg]
total weight propulsion system : 2462 [kg](18.4 [%])
***************************************************************
fuselage aluminium frame : 1231 [kg]
cabin layout : pitch : 87 [cm] (2+2) seating in 9.5 rows
weight two toilets : 16 [kg]
weight 4 fire extinguisher : 12 [kg]
weight pantry : 21.9 [kg]
weight racks for hand luggage : 19.0 [kg]
weight 19.0 windows : 17.10 [kg]
passenger cabin width : 2.69 [m] cabin length : 9.37 [m] cabin height : 1.90 [m]
weight cabin furbishing : 151.16 [kg]
weight cabin floor : 161.07 [kg]
bracing : 212.8 [kg]
fuselage covering ( 141.4 [m2] duraluminium 0.75 [mm]) : 280.0 [kg]
weight radio navigation equipment : 7.0 [kg]
weight instruments. : 4.0 [kg]
weight lighting : 9.5 [kg]
weight controls : 13.4 [kg]
weight seats : 210.0 [kg]
weight air conditioning : 57 [kg]
total weight fuselage : 2415 [kg](18.1 [%])
***************************************************************
weight wing covering (doped linen fabric) : 207 [kg]
total weight aluminium ribs (146 ribs) : 477 [kg]
weight engine mounts : 83 [kg]
weight fuel tanks empty for total 2036 [litre] fuel : 163 [kg]
load on front upper spar (clmax) per running metre : 1437.3 [N]
load on rear upper spar (vmax) per running metre : 890.8 [N]
total weight 8 aluminium spars : 622 [kg]
weight wings : 1306 [kg]
weight wing/square meter : 4.70 [kg]
weight 12 Warren truss interplane struts : 642.1 [kg]
weight fin & rudder (18.2 [m2]) : 88.4 [kg]
weight stabilizer & elevator (31.2 [m2]): 149.0 [kg]
total weight wing surfaces & bracing : 2431 [kg] (18.2 [%])
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wheel pressure : 6690.0 [kg]
weight 2 wheels (1560 [mm] by 312 [mm]) : 440.0 [kg]
weight tail wheel : 34.2 [kg]
weight undercarriage with axle 176.5 [kg]
total weight landing gear : 650.7 [kg] (4.9 [%]
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calculated empty weight : 7959 [kg](59.5 [%])
weight oil for 4.3 hours flying : 178.5 [kg]
calculated operational weight empty : 8138 [kg] (60.8 [%])
published operational weight empty : 8047 [kg] (60.1 [%])
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weight crew : 324 [kg]
weight fuel for 2.0 hours flying : 817 [kg]
weight catering : 54.6 [kg]
weight water : 21.9 [kg]
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operational weight empty: 9355 [kg](69.9 [%])
weight 38 passengers : 2926 [kg]
weight luggage & freight : 874 [kg]
operational weight loaded: 13155 [kg](98.3 [%])
fuel reserve : 224.7 [kg] enough for 0.55 [hours] flying
operational weight fully loaded : 13380 [kg] with fuel tank filled for 63 [%]
published maximum take-off weight : 13380 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 8.08 [kg/kW]
power loading (operational without useful load) : 5.65 [kg/kW]
power loading (Take-off) 1 PUF: 10.78 [kg/kW]
total power : 1655.5 [kW] at 2200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.9 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]
design flight time : 2.88 [hours]
design cycles : 2716 sorties, design hours : 7812 [hours]
operational wing loading : 330 [N/m^2]
wing stress (3 g) during operation : 211 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.38 ["]
max. angle of attack (stalling angle) : 11.80 ["]
angle of attack at max. speed : 0.57 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.12 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
lift coefficient at max. speed : 0.17 [ ]
induced drag coefficient at max. speed : 0.0014 [ ]
drag coefficient at max. speed : 0.0332 [ ]
drag coefficient (zero lift) : 0.0317 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 12972 [kg]): 92 [km/u]
landing speed at sea-level: 108 [km/hr]
min. drag speed (max endurance) : 122 [km/hr] at 2000 [m](power :34 [%])
min. power speed (max range) : 122 [km/hr] at 2000 [m] (power:34 [%])
max. rate of climb speed : 117.5 [km/hr] at sea-level
cruising speed : 184 [km/hr] op 2000 [m] (power:71 [%])
design speed prop : 194 [km/hr]
maximum speed : 204 [km/hr] op 100 [m] (power:104 [%])
climbing speed at sea-level : 391 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 112.2 [km/u]
static prop wash : 135 [km/u]
take-off distance at sea-level : 183 [m]
lift/drag ratio : 12.55 [ ]
climb to 1000m with max payload : 4.17 [min]
climb to 2000m with max payload : 8.84 [min]
climb to 3000m with max payload : 14.43 [min]
practical ceiling (operational weight 9355 [kg] ) : 8243 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:13176 [kg] ) : 6473 [m]
calculation *10* (action radius & endurance)
published range : 660 [km] with 4 crew and 3449.9 [kg] useful load and 88.1 [%] fuel
range : 503 [km] with 4 crew and 3800.0 [kg] useful load and 67.1 [%] fuel
range : 725 [km] with 38.0 passengers with each 10 [kg] luggage and 96.7 [%] fuel
Available Seat Kilometers (ASK) : 27538 [paskm]
max range theoretically with additional fuel tanks total 7040.9 [litre] fuel : 2320 [km]
useful load with range 500km : 4049 [kg]
useful load with range 500km : 38 passengers
production (useful load): 743.36 [tonkm/hour]
production (passengers): 6976.80 [paskm/hour]
oil and fuel consumption per tonkm : 0.61 [kg]
oil and fuel consumption per paskm : 0.06 [kg]
fuel cost per paskm : 0.06 [eur]
crew cost per paskm : 0.04 [eur]
time between engine failure : 25 [hr]
writing off per paskm : 0.10 [eur]
insurance per paskm : 0.05 [eur]
maintenance cost per paskm : 0.57 [eur]
direct operating cost per paskm : 0.82 [eur]
direct operating cost per tonkm : 8.18 [eur]
Literature :
Piston-engined airliners page 25,26,27
Praktisch handboek vliegtuigen deel 2 page 94,95
Wikipedia
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 10 May 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4