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weight and performance calculations for the Boeing 40A
Boeing 40A
role : medium weight passenger aircraft
importance : ****
first flight : 20 July 1925 operational : July 1927
country : United States of America
design :
production : A & B model 82 aircraft
general information :
Combined mail and passenger aircraft. Could carry two passengers and 540 kg mail. The Boeing 40A was the first US civil aircraft using the now legendary Pratt & Whitney Wasp engine. The Boeing 40B had a 525 hp Pratt & Whitney Hornet engine, entering service in September 1929. It could carry 3 passenger at a cruising speed of 201 km/hr over a distance of 861 km
users : Boeing air transport
crew : 1 passengers : 2
engine : 1 Pratt & Whitney R-1340-C1 Wasp air-cooled 9 -cylinder radial engine 420 [hp](313.2 KW)
compressor height 500
dimensions :
wingspan : 13.47 [m], length : 10.14 [m], height : 3.55[m]
wing area : 50.82 [m^2]
weights :
max.take-off weight : 2727 [kg]
empty weight operational : 1605 [kg] useful load : 720 [kg]
performance :
maximum speed :206 [km/hr] at sea-level
cruise speed :185 [km/u] op 100 [m]
service ceiling : 4420 [m]
range : 1046 [km]
description :
2-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
engines, landing gear, fuel and useful load in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.67 [ ]
diameter airscrew 3.05 [m]
angle of attack prop : 13.44 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 2000 [r.p.m.]
pitch at Max speed 1.72 [m]
blade-tip speed at Vmax and max revs. : 324 [m/s]
calculation : *1* (dimensions)
wing chord : 2.01 [m]
mean wing chord : 1.89 [m]
calculated wing chord (rounded tips): 2.09 [m]
wing aspect ratio : 7.14 []
estimated gap : 1.67 [m]
gap/chord : 0.89 [ ]
seize (span*length*height) : 485 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 5.0 [kg/hr]
fuel consumption(cruise speed) : 72.0 [kg/hr] (98.2 [litre/hr]) at 71 [%] power
distance flown for 1 kg fuel : 2.58 [km/kg] at 2210 [m] height, sfc : 323.4 [kg/kwh]
estimated total fuel capacity : 629 [litre] (461 [kg])
calculation : *3* (weight)
weight engine(s) dry : 340.0 [kg] = 1.09 [kg/KW]
weight 45.6 litre oil tank : 3.88 [kg]
oil tank filled with 2.3 litre oil : 2.1 [kg]
oil in engine 1.7 litre oil : 1.6 [kg]
fuel in engine 2.1 litre fuel : 1.57 [kg]
weight 41.8 litre gravity patrol tank(s) : 6.3 [kg]
weight inertia starter : 7.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 37.9 [kg]
total weight propulsion system : 397 [kg](14.6 [%])
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fuselage skeleton (steel tubes) : 6.50 [cm]): 337 [kg]
cabin layout : pitch : 87 [cm] (1+0) seating in 2.0 rows
weight 4.0 windows : 3.60 [kg]
passenger cabin width : 0.89 [m] cabin length : 1.74 [m] cabin height : 1.40 [m]
weight cabin furbishing : 4.13 [kg]
weight cabin floor : 9.91 [kg]
bracing : 24.1 [kg]
fuselage covering ( 19.4 [m2] doped linen fabric) : 6.0 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 5.5 [kg]
weight seats : 15.0 [kg]
weight 587 [litre] main fuel tank empty : 47.0 [kg]
Length : 33 ft 3.25 in = 10.14m span : 44ft 2.25 in = 13.47m Chord : 6 ft 7 in = 2.01m airscrew : 10 ft = 3.05m height : 11 ft 8 in = 3.55m
weight air conditioning : 3 [kg]
weight engine mounts & firewalls : 16 [kg]
total weight fuselage : 475 [kg](17.4 [%])
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weight plywood wing covering : 76 [kg]
total weight ribs (79 ribs) : 162 [kg]
load on front upper spar (clmax) per running metre : 1898.9 [N]
load on rear upper spar (vmax) per running metre : 581.5 [N]
total weight 8 spars : 197 [kg]
weight wings : 435 [kg]
weight wing/square meter : 8.57 [kg]
weight 8 interplane struts & cabane : 37.0 [kg]
weight cables (78 [m]) : 24.2 [kg] (= 311 [gram] per metre)
diameter cable : 7.1 [mm]
weight fin & rudder (2.1 [m2]) : 18.4 [kg]
weight stabilizer & elevator (5.7 [m2]): 49.4 [kg]
total weight wing surfaces & bracing : 564 [kg] (20.7 [%])
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wheel pressure : 1363.5 [kg]
weight 2 wheels (880 [mm] by 135 [mm]) : 62.3 [kg]
weight tailskid : 7.7 [kg]
weight undercarriage with axle 80.5 [kg]
total weight landing gear : 150.5 [kg] (5.5 [%]
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calculated empty weight : 1587 [kg](58.2 [%])
weight oil for 6.8 hours flying : 33.9 [kg]
calculated operational weight empty : 1620 [kg] (59.4 [%])
published operational weight empty : 1605 [kg] (58.9 [%])
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weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 144 [kg]
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operational weight empty: 1845 [kg](67.7 [%])
weight 2 passengers : 154 [kg]
weight luggage & freight : 566 [kg]
operational weight loaded: 2565 [kg](67.7 [%])
fuel reserve : 161.6 [kg] enough for 2.24 [hours] flying
operational weight fully loaded : 2727 [kg] with fuel tank filled for 66 [%]
published maximum take-off weight : 2727 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 8.71 [kg/kW]
power loading (operational without useful load) : 5.89 [kg/kW]
total power : 313.2 [kW] at 2000 [r.p.m]
Restored and airworthy Boeing 40C, c/n 1043, the oldest flying Boeing in the world.
calculation : *5* (loads)
manoeuvre load : 3.7 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.5 [g]
design flight time : 3.95 [hours]
design cycles : 5161 sorties, design hours : 20381 [hours]
operational wing loading : 356 [N/m^2]
wing stress (3 g) during operation : 125 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.20 ["]
max. angle of attack (stalling angle) : 12.58 ["]
angle of attack at max. speed : 0.95 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max. speed : 0.18 [ ]
induced drag coefficient at max. speed : 0.0025 [ ]
drag coefficient at max. speed : 0.0363 [ ]
drag coefficient (zero lift) : 0.0337 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 2655 [kg]): 97 [km/u]
landing speed at sea-level: 114 [km/hr]
min. drag speed (max endurance) : 144 [km/hr] at 2210 [m](power :51 [%])
min. power speed (max range) : 144 [km/hr] at 2210 [m] (power:51 [%])
max. rate of climb speed : 122.1 [km/hr] at sea-level
cruising speed : 185 [km/hr] op 2210 [m] (power:75 [%])
design speed prop : 196 [km/hr]
maximum speed : 206 [km/hr] op 100 [m] (power:108 [%])
climbing speed at sea-level : 381 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 118.3 [km/u]
static prop wash : 167 [km/u]
take-off distance at sea-level : 165 [m]
lift/drag ratio : 9.67 [ ]
climb to 1000m with max payload : 5.58 [min]
climb to 2000m with max payload : 13.54 [min]
climb to 3000m with max payload : 24.89 [min]
practical ceiling (operational weight 1845 [kg] ) : 6358 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:2691 [kg] ) : 4183 [m]
max. dive speed : 437.1 [km/hr] at 3183 [m] height
turning speed at CLmax : 126.2 [km/u] at 50 [m] height
turn radius at 50m: 57 [m]
time needed for 360* turn 10.2 [seconds] at 50m
load factor at max. angle turn 2.41 ["g"]
calculation *10* (action radius & endurance)
published range : 1046 [km] with 1 crew and 619.4 [kg] useful load and 88.1 [%] fuel
range : 787 [km] with 1 crew and 720.0 [kg] useful load and 66.3 [%] fuel
range : 2193 [km] with 2.0 passengers with each 10 [kg] luggage and 184.7 [%] fuel
Available Seat Kilometers (ASK) : 4386 [paskm]
max range theoretically with additional fuel tanks for total 1399.1 [litre] fuel : 2641.2 [km]
useful load with range 500km : 831 [kg]
useful load with range 500km : 2 passengers
production (useful load): 154.15 [tonkm/hour]
production (passengers): 370.80 [paskm/hour]
oil and fuel consumption per tonkm : 0.50 [kg]
oil and fuel consumption per paskm : 0.21 [kg]
fuel cost per paskm : 0.21 [eur]
crew cost per paskm : 0.40 [eur]
_
I=_°°°/
°
economic hours : 12775 [hours] is less then design hours
time between engine failure : 195 [hr]
writing off per paskm : 0.25 [eur]
insurance per paskm : 0.1733 [eur]
rigging cost per paskm : 0.0159 [eur]
maintenance cost per paskm : 0.6650 [eur]
direct operating cost per paskm : 1.70 [eur]
Literature :
Wikipedia
Piston-engined airliners page
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