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weight and performance calculations for the Vickers Viking Ib
Vickers Viking Ib
role : regional airliner
importance : ****
first flight : 22 June 1945 G-AGOK flown by “Mutt” Summers at Wisley Airfield
Viking Ib : 6 Augustus 1946 operational : September 1946
country : United-Kingdom
design : R.K. Pierson
production : Viking Ib : 113 aircraft total : 161 until 1948
general information :
The Viking was designed as transport aircraft on request of the British government.
Parts of the Wellington bomber were used, such as the geodetic wing , motors and
undercarriage. At first the geodetic wing was covered with fabric, later version had an aluminum skin. The fuselage was unpressurized. The prototype G-AGOK crashed on 23 April 1946 due to a double engine failure. BOAC (BEA division) placed an order of 19 pieces on the Viking I and later an order of 13 pieces on the Ia, a version with a newly designed all-metal wing. The Viking Ib had a longer fuselage nose, allowing for 3 more passengers, making it first flight August 6th, 1946.
The Viking was a sturdy, reliable work horse which served successfully for many years. BEA operated the Viking until 1954.
Fuel capacity : 750 imp.gallon = 3410 liters. TO distance over 15 [m] : 780 [m] landing distance over 15 [m] : 1200 [m] Propellor : 4-bladed 4.04m diameter
TKS leading edge ice protection.
Later cabin arrangement was changed to a 36 seat lay-out, 9 rows in 2+2 seating
primary users : BEA, DDL, Central African Airways, Air India, Aer Lingus
flight crew : 3 cabin crew : 1 passengers : 24 - 36
flight crew consist of pilot, co-pilot and radio operator
powerplant : 2 Bristol Hercules 634 air-cooled 14 -cylinder radial engine 1690 [hp]
(1260.2 KW) normal rating, supercharged engine, high blower, constant power to
height : 3200 [m] and with 2000 [hp](1491.4 KW) available for take-off
dimensions :
wingspan : 27.2 [m], length : 19.86 [m], height : 5.97 [m]
wing area : 81.9 [m^2]
weights :
max.take-off weight : 15422 [kg]
empty weight operational : 10433 [kg] useful load : 3016 [kg]
performance :
maximum continuous speed : 423 [km/u] op 3200 [m]
normal cruise speed : 340 [km/u] op 1830 [m] (65 [%] power)
service ceiling : 7240 [m]
range with max fuel : 1608 [km] and allowance for 47.1 [km] diversion and 30 [min]
hold
description :
low-winged monoplane with retractable landing gear with tail wheel
tapered wing with slotted flaps airfoil : RAF
engines and landing gear attached to the wings, fuel tanks in the wings
construction : all-metal stressed-skin (Alclad-aluminium) airplane
fuselage shape : 0
airscrew :
two Hamilton Standard constant speed 4 -bladed tractor airscrews
max. efficiency :0.69 [ ]
diameter airscrew 4.04 [m]
relative pitch (J) : 1.42 [ ]
power loading prop : 155.97 [KW/m]
theoretical pitch without slip : 6.42 [m]
blade angle prop at max.speed : 35.01 [ ]
tip-speed close to speed of sound (above Mach 0.85) > loose of efficiency
reduction : 0.44 [ ]
airscrew revs : 1232 [r.p.m.]
aerodynamic pitch at max. continuous speed 5.72 [m]
blade-tip speed at max.continuous speed : 286 [m/s]
propellor noise in flight : 99 [Db]
calculation : *1* (dimensions)
measured wing chord : 2.94 [m] at 50% wingspan
mean wing chord : 3.01 [m]
calculated average wing chord tapered wing with rounded tips: 2.96 [m]
wing aspect ratio : 9.0 []
seize (span*length*height) : 3225 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 27.7 [kg/hr]
fuel consumption (econ. cruise speed) : 465.7 [kg/hr] (635.4 [litre/hr]) at 65 [%] power
distance flown for 1 kg fuel : 0.73 [km/kg] at 1830 [m] height, sfc : 286.0 [kg/kwh]
estimated total fuel capacity : 3411 [litre] (2500 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 1788.0 [kg] = 0.71 [kg/KW]
weight 238.3 litre oil tank : 20.25 [kg]
oil tank filled with 18.9 litre oil : 17.0 [kg]
oil in engine 14.0 litre oil : 12.6 [kg]
fuel in engine 17.2 litre fuel : 12.60 [kg]
weight 270.1 litre gravity patrol tank(s) : 40.5 [kg]
weight Burgess type silencers : 50.4 [kg]
weight Rotax starter : 30.9 [kg]
weight NACA cowling 56.5 [kg]
weight variable pitch control : 17.3 [kg]
weight airscrew(s) incl. boss & bolts : 488.4 [kg]
total weight propulsion system : 2517 [kg](16.3 [%])
***************************************************************
fuselage aluminium frame : 1764 [kg]
cabin layout : pitch : 81 [cm] (2+1) seating in 8.0 rows
pax density (normal seating) : 1.13 [m2/pax]
high density seating passengers : 43 at 4 -abreast seating in 10.8 rows
weight 1 toilets : 8.0 [kg]
weight 2 hand fire extinguisher : 6 [kg]
weight buffet : 20.7 [kg]
weight 18 windows : 16.2 [kg]
weight 4 emergency exits : 12.0 [kg]
weight 1 entrance/exit doors : 5.0 [kg]
extra main deck space for freight/mail/luggage etc. : 5.07 [m3]
cabin volume (usable), excluding flight deck : 48.65 [m3]
passenger cabin max.width : 2.55 [m] cabin length : 10.63 [m] cabin height : 1.90 [m]
fuselage covering ( 108.0 [m2] duraluminium 4.03 [mm]) : 1143.5 [kg]
weight floor beams : 25.5 [kg]
weight cabin furbishing : 112.9 [kg]
weight cabin floor : 96.1 [kg]
fuselage (sound proof) isolation : 35.6 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight radio direction finding (RDF) equipment : 5.0 [kg]
weight artificial horizon : 1.1 [kg]
weight instruments. : 11.0 [kg]
weight lighting : 6.0 [kg]
weight electricity generator : 13.7 [kg]
weight controls : 9.8 [kg]
weight seats : 140.0 [kg]
weight air conditioning : 36 [kg]
total weight fuselage : 3421 [kg](22.2 [%])
***************************************************************
total weight aluminium ribs (262 ribs) : 550 [kg]
weight engine mounts : 126 [kg]
weight two 1570 [litre] main fuel tanks empty : 251.3 [kg]
weight wing covering (painted aluminium 2.12 [mm]) : 939 [kg]
total weight aluminium spars (multi-cellular wing structure) : 887 [kg]
weight wings : 2375 [kg]
weight wing/square meter : 29.00 [kg]
weight rubber de-icing boots : 29.9 [kg]
weight fin & rudder (8.6 [m2]) : 250.4 [kg]
weight stabilizer & elevator (9.2 [m2]): 267.8 [kg]
weight slotted flaps (6.8 [m2]) : 105.0 [kg]
total weight wing surfaces & bracing : 3406 [kg] (22.1 [%])
*******************************************************************
wheel pressure : 7711.0 [kg]
weight 2 Dunlop main wheels (1290 [mm] by 198 [mm]) : 483.9 [kg]
weight tailwheel(s) : 5.9 [kg]
weight hydraulic wheel-brakes : 13.4 [kg]
weight Dowty shock absorbers : 17.9 [kg]
weight wheel hydraulic operated retraction system : 80.5 [kg]
weight undercarriage struts with axle 364.7 [kg]
total weight landing gear : 966.3 [kg] (6.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 10310 [kg](66.9 [%])
weight oil for 5.7 hours flying : 157.3 [kg]
calculated operational weight empty : 10468 [kg] (67.9 [%])
published operational weight empty : 10433 [kg] (67.7 [%])
weight crew : 324 [kg]
weight fuel for 2.0 hours flying : 931 [kg]
weight catering : 39.7 [kg]
weight water : 15.9 [kg]
********************************************************************
operational weight empty: 11779 [kg](76.4 [%])
weight 24 passengers : 1848 [kg]
weight luggage : 293 [kg]
weight cargo : 875 [kg]
operational weight loaded: 14795 [kg](95.9 [%])
fuel reserve : 627.4 [kg] enough for 1.35 [hours] flying
operational weight fully loaded : 15422 [kg] with fuel tank filled for 62 [%]
published maximum take-off weight : 15422 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 5.17 [kg/kW]
power loading (operational without useful load) : 4.67 [kg/kW]
power loading (Take-off) 1 PUF: 10.34 [kg/kW]
max.total take-off power : 2982.8 [kW]
calculation : *5* (loads)
manoeuvre load : 3.1 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.1 [g]
design flight time : 3.31 [hours]
design cycles : 9351 sorties, design hours : 30957 [hours]
operational wing loading : 1780 [N/m^2]
wing stress (3 g) during operation : 184 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.36 ["]
max. angle of attack (stalling angle, clean) : 11.50 ["]
max. angle of attack (full flaps) : 10.61 ["]
angle of attack at max. speed : 1.24 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.12 [ ]
lift coefficient at max. speed : 0.23 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
max.lift coefficient full flaps : 1.39 [ ]
induced drag coefficient at max.speed : 0.0024 [ ]
drag coefficient at max. speed : 0.0284 [ ]
drag coefficient (zero lift) : 0.0260 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 14956 [kg]): 183 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 162 [km/u]
landing speed at sea-level (normal landing weight : 14305 [kg]): 186 [km/hr]
max. rate of climb speed : 186 [km/hr] at sea-level
max. endurance speed : 187 [km/u] min.fuel/hr : 222 [kg/hr] at height : 610 [m]
max. range speed : 267 [km/u] min. fuel consumption : 1.109 [kg/km] at cruise height :
3962 [m]
cruising speed : 340 [km/hr] at 1830 [m] (power:65 [%])
max. continuous speed* : 423.00 [km/hr] at 3200 [m] (power:100 [%])
climbing speed at sea-level (loaded) : 490 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 139 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 222.5 [km/u]
emergency/TO power : 2000 [hp] at 2800 [rpm]
static prop wash : 176 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 591 [m]
take-off distance at sea-level over 15 [m] height : 686 [m]
landing run : 687 [m]
landing run from 15 [m] : 1343 [m]
lift/drag ratio : 14.43 [ ]
climb to 1000m with max payload : 2.25 [min]
climb to 2000m with max payload : 4.55 [min]
climb to 3000m with max payload : 6.92 [min]
climb to 5000 [m] with max payload : 15.43 [min]
practical ceiling (operational weight empty 11779 [kg] ) : 8800 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:15189 [kg] ) : 7400 [m]
calculation *10* (action radius & endurance)
published range : 1608 [km] with 4 crew and 2427.9 [kg] useful load and 88.1 [%] fuel (no reserves)
Remains of G-AIVE which crashed on 21 April 1948 in Scottland.
range : 1179 [km] with 4 crew and 3016.0 [kg] useful load and 64.6 [%] fuel
range : 1818 [km] with 24.0 passengers with each 12.2 [kg] luggage and 99.6 [%] fuel
Available Seat Kilometres (ASK) : 43622 [paskm]
max range theoretically with additional fuel tanks total 6648.7 [litre] fuel : 4395 [km]
useful load with range 500km : 4189 [kg]
useful load with range 500km : 24 passengers
production (theor.max load): 1424 [tonkm/hour]
production (useful load): 1025 [tonkm/hour]
production (passengers): 8160 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.346 [kg]
fuel cost per paskm : 0.060 [eur]
crew cost per paskm : 0.037 [eur]
economic hours : 18250 [hours] is less then design hours
time between engine failure : 2410 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.058 [eur]
insurance per paskm : 0.0014 [eur]
maintenance cost per paskm : 0.133 [eur]
direct operating cost per paskm : 0.289 [eur]
direct operating cost per tonkm (max. load): 1.658 [eur]
direct operating cost per tonkm (normal useful load): 2.302 [eur]
literature :
piston engined airliners page 60,61
Verkeersvliegtuigen Moussault page 16, 96
prakt. handb. vliegt. deel 5 page 114,115
Vickers VC.1 Viking – Wikipedia
Aeroplane monthly October 1992
* max. continuous speed : max. level speed maintainable for minimal 30 min.
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 03 April 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4