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weight and performance calculations for the Airspeed A.S.57 Ambassador
Airspeed A.S.57 Ambassador
role : commuter prop 50
importance : **
first flight : 10 July 1947 G-AGUA flown by George B.S.Errington
operational : March 1952
country : United-Kingdom
design :
production : 23 aircraft
general information :
Despite the fact that the first flight was made in 1947, it took until March 13, 1952 before this elegant aircraft entered service with BEA. It remained in service with this company until 30 July 1958. During this time, 2.5 million passengers were transported with 20 Amassadors. They also flew to Amsterdam. Despite the good performance and the beautiful appearance, it entered service too late to become a success. It was outperformed by the turboprop-powered Vickers Viscount.
Fuel capacity : 7200 litre. By December 1955 the Ambassadors had flown 2230 flying hours annually for BEA.
primary users : BEA, later used for charter and scheduled flights by BKS Air Transport,
Autair , Butler Air Transport, Globe Air, Shell Petroleum and Dan-air
flight crew : 2 cabin crew : 1 passengers : 50
powerplant : 2 Bristol Centaurus 661 air-cooled 18 -cylinder radial engine 1775
[hp](1323.6 KW) normal rating, supercharged engine, high blower, constant power to
height : 6706 [m] and with 2625 [hp](1957.5 KW) available for take-off
dimensions :
wingspan : 33.05 [m], length : 24.99 [m], height : 5.74 [m]
wing area : 111.5 [m^2]
weights :
max.take-off weight : 24948 [kg]
empty weight operational : 16277 [kg] useful load : 5500 [kg]
performance :
maximum continuous speed : 502 [km/u] op 6706 [m]
normal cruise speed : 463 [km/u] op 5800 [m] (85 [%] power)
service ceiling : 10500 [m]
range with max fuel : 3325 [km] and allowance for 217.4 [km] diversion and 30 [min] hold
description :
high-winged monoplane with retractable landing gear with nose wheel
tapered multi-cellular wing with flush-riveted stressed skin
with Fowler flaps airfoil : NACA
with near-laminar flow
engines and landing gear attached to the wings, fuel tanks in the wings
construction : all-metal aluminium-alloy stressed-skin construction with pressurized
fuselage fuselage shape : O
airscrew :
two Hamilton Standard constant speed 4 -bladed tractor airscrews with max. efficiency
:0.71 [ ]
estimated diameter airscrew 4.50 [m]
relative pitch (J) : 1.94 [ ]
power loading prop : 147.07 [KW/m]
theoretical pitch without slip : 9.69 [m]
blade angle prop at max.speed : 43.42 [ ]
reduction : 0.40 [ ]
airscrew revs : 960 [r.p.m.]
aerodynamic pitch at max. continuous speed 8.72 [m]
blade-tip speed at max.continuous speed : 266 [m/s]
propellor noise in flight : 92 [Db]
calculation : *1* (dimensions)
measured wing chord : 2.87 [m] at 50% wingspan
mean wing chord : 3.37 [m]
calculated average wing chord tapered wing with rounded tips: 3.34 [m]
wing aspect ratio : 9.8 []
seize (span*length*height) : 4741 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 26.5 [kg/hr]
fuel consumption (econ. cruise speed) : 648.5 [kg/hr] (884.8 [litre/hr]) at 85 [%] power
distance flown for 1 kg fuel : 0.71 [km/kg] at 5800 [m] height, sfc : 288.0 [kg/kwh]
estimated total fuel capacity : 7212 [litre] (5286 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 2444.0 [kg] = 0.92 [kg/KW]
weight 320.3 litre oil tank : 27.23 [kg]
oil tank filled with 19.9 litre oil : 17.8 [kg]
oil in engine 14.7 litre oil : 13.2 [kg]
fuel in engine 18.1 litre fuel : 13.24 [kg]
weight 376.2 litre gravity patrol tank(s) : 56.4 [kg]
weight jet stacks : 66.2 [kg]
weight Rotax starter : 32.4 [kg]
weight NACA cowling 59.3 [kg]
weight variable pitch control : 21.7 [kg]
weight airscrew(s) incl. boss & bolts : 610.6 [kg]
total weight propulsion system : 3340 [kg](13.4 [%])
***************************************************************
fuselage aluminium frame : 3208 [kg]
typical cabin layout for 50 passengers : pitch : 81 [cm] ( 2+2 ) seating in 12.5 rows
pax density (normal seating) : 0.92 [m2/pax]
high density seating passengers : 79 at 5 -abreast seating in 15.9 rows
weight 1 toilets : 10.0 [kg]
weight 4 hand fire extinguisher : 12 [kg]
weight buffet : 65.4 [kg]
weight 27 windows : 24.3 [kg]
weight 4 emergency exits : 12.0 [kg]
weight 2 life rafts : 62.5 [kg]
weight oxygen masks & oxygen generators : 32.5 [kg]
weight emergency flare installation : 10 [kg]
weight emergency evacuation slide : 15 [kg]
weight 2 entrance/exit doors : 24.0 [kg]
weight 2 freight doors (belly) : 8.0 [kg]
weight ladies" powder room : 16 [kg]
weight men"s dressing room : 12 [kg]
weight diplomatic mail locker : 2 [kg]
extra main deck space for freight/mail/luggage etc. : 4.20 [m3]
cabin volume (usable), excluding flight deck : 95.72 [m3]
passenger cabin max.width : 2.95 [m] cabin length : 15.66 [m] cabin height : 2.36 [m]
pressure at cruise height 6100.00 [m] : 0.47 [kg/cm2] cabin pressure : 0.86 [kg/cm2]
weight rear pressure bulkhead : 104.4 [kg]
weight air pressurization system : 27.3 [kg]
fuselage covering ( 169.6 [m2] duraluminium 2.57 [mm]) : 1144.6 [kg]
weight floor beams : 92.6 [kg]
weight cabin furbishing : 275.8 [kg]
weight cabin floor : 315.0 [kg]
fuselage (sound proof) isolation : 54.4 [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 APU / engine starter: 66.2 [kg]
weight lighting : 12.5 [kg]
weight electricity generator : 12.5 [kg]
weight controls : 11.9 [kg]
weight seats : 265.0 [kg]
weight air conditioning : 75 [kg]
total weight fuselage : 5895 [kg](23.6 [%])
***************************************************************
total weight aluminium ribs (378 ribs) : 890 [kg]
weight engine mounts : 132 [kg]
weight two 3418 [litre] main fuel tanks empty : 546.9 [kg]
weight wing covering (painted aluminium 2.25 [mm]) : 1356 [kg]
total weight aluminium spars (multi-cellular wing structure) : 1527 [kg]
weight wings : 3772 [kg]
weight wing/square meter : 33.83 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 36.4 [kg]
weight fin & rudder (12.7 [m2]) : 430.8 [kg]
weight stabilizer & elevator (12.5 [m2]): 425.2 [kg]
weight flight control hydraulic servo actuators: 28.7 [kg]
weight fowler flaps (9.3 [m2]) : 163.2 [kg]
total weight wing surfaces & bracing : 5536 [kg] (22.2 [%])
*******************************************************************
wheel pressure : 12474.0 [kg]
weight 2 Dunlop main wheels (1040 [mm] by 160 [mm]) : 682.1 [kg]
weight nose wheel : 85.3 [kg]
weight hydraulic wheel-brakes : 21.8 [kg]
weight pneumatic-hydraulic shock absorbers : 29.0 [kg]
weight wheel hydraulic operated retraction system : 89.4 [kg]
weight undercarriage struts with axle 421.3 [kg]
total weight landing gear : 1341.2 [kg] (5.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 16113 [kg](64.6 [%])
weight oil for 8.6 hours flying : 228.1 [kg]
calculated operational weight empty : 16341 [kg] (65.5 [%])
published operational weight empty : 16277 [kg] (65.2 [%])
weight crew : 243 [kg]
weight fuel for 2.0 hours flying : 1297 [kg]
weight catering : 125.7 [kg]
weight water : 100.5 [kg]
********************************************************************
operational weight empty: 18107 [kg](72.6 [%])
weight 50 passengers : 3850 [kg]
weight luggage : 610 [kg]
weight cargo : 1040 [kg]
operational weight loaded: 23607 [kg](94.6 [%])
fuel reserve : 1341.1 [kg] enough for 2.07 [hours] flying
operational weight fully loaded : 24948 [kg] with fuel tank filled for 50 [%]
published maximum take-off weight : 24948 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 6.37 [kg/kW]
power loading (operational without useful load) : 6.84 [kg/kW]
power loading (Take-off) 1 PUF: 12.75 [kg/kW]
max.total take-off power : 3914.9 [kW]
calculation : *5* (loads)
manoeuvre load : 3.6 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.9 [g]
design flight time : 5.03 [hours]
design cycles : 7128 sorties, design hours : 35834 [hours]
operational wing loading : 2101 [N/m^2]
wing stress (3 g) during operation : 186 [N/kg] at 3g emergency manoeuvre
Crashed G-AMAB 08 april 1955 at Dusseldorf
calculation : *6* (angles of attack)
angle of attack zero lift : -1.34 ["]
max. angle of attack (stalling angle, clean) : 11.21 ["]
max. angle of attack (full flaps) : 10.32 ["]
angle of attack at max. speed : 1.66 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.12 [ ]
lift coefficient at max. speed : 0.27 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
max.lift coefficient full flaps : 1.56 [ ]
induced drag coefficient at max.speed : 0.0031 [ ]
drag coefficient at max. speed : 0.0186 [ ]
drag coefficient (zero lift) : 0.0155 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 24299 [kg]): 200 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 138 [km/u]
landing speed at sea-level (normal landing weight : 22833 [kg]): 159 [km/hr]
max. rate of climb speed : 205 [km/hr] at sea-level
max. endurance speed : 206 [km/u] min.fuel/hr : 304 [kg/hr] at height : 610 [m]
max. range speed : 422 [km/u] min. fuel consumption : 1.278 [kg/km] at cruise height :
8839 [m]
cruising speed : 463 [km/hr] at 5800 [m] (power:89 [%])
max. continuous speed* : 502.00 [km/hr] at 6706 [m] (power:100 [%])
climbing speed at sea-level (loaded) : 280 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 97 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 223.1 [km/u]
emergency/TO power : 2625 [hp] at 2700 [rpm]
static prop wash : 172 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 766 [m]
take-off distance at sea-level over 15 [m] height : 949 [m]
landing run : 497 [m]
landing run from 15 [m] : 1058 [m]
lift/drag ratio : 19.41 [ ]
climb to 1000m with max payload : 4.20 [min]
climb to 2000m with max payload : 8.59 [min]
climb to 3000m with max payload : 13.20 [min]
climb to 5000 [m] with max payload : 23.66 [min]
practical ceiling (operational weight empty 18107 [kg] ) : 10400 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:24624 [kg] ) : 8500 [m]
calculation *10* (action radius & endurance)
published range : 3325 [km] with 3 crew and 3706.9 [kg] useful load and 88.1 [%]
fuel (no reserves)
range : 2045 [km] with 3 crew and 5500.0 [kg] useful load and 54.2 [%] fuel
range : 2787 [km] with 50.0 passengers with each 12.2 [kg] luggage and 73.9 [%] fuel
Available Seat Kilometres (ASK) : 139367 [paskm]
max range theoretically with additional fuel tanks total 11632.1 [litre] fuel : 6674 [km]
useful load with range 500km : 7826 [kg]
useful load with range 500km : 50 passengers
production (theor.max load): 3623 [tonkm/hour]
production (useful load): 2546 [tonkm/hour]
production (passengers): 23150 [paskm/hour]
oil and fuel consumption per tonkm : 0.186 [kg]
fuel cost per paskm : 0.029 [eur]
crew cost per paskm : 0.013 [eur]
economic hours : 18250 [hours] is less then design hours
time between engine failure : 2502 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.032 [eur]
insurance per paskm : 0.0005 [eur]
maintenance cost per paskm : 0.102 [eur]
direct operating cost per paskm : 0.177 [eur]
direct operating cost per tonkm (max. load): 1.130 [eur]
direct operating cost per tonkm (normal useful load): 1.607 [eur]
Literature :
piston engined airliners page 60,61
praktisch handboek vliegtuigen deel 5 page123
verkeersvliegtuigen Moussault page 28
verkeersvliegtuigen B.van der Klaauw page 5
verkeersvliegtuigen nu en straks page 5
Jane’s fighting aircraft WWII page 102
* 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