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weight and performance calculations for the Breguet 14T
Breguet 14T
role : air taxi
importance : ****
first flight : operational : April 1919
country : France
design :
production : 106 aircraft
general information :
One of the first France passenger aircraft after WWI. Developed from the WWI Breguet 14 bomber. It was popular and stayed in service till 1923. It flew on routes Paris – Liege and Paris – Marseille, Paris – Bruxelles and Paris - London
users : CMA, Air Union , Lignes Aerienes Latecoere
crew : 1 passengers : 2
engine : 1 Renault 12 Fcx liquid-cooled 12 -cylinder V-engine 300 [hp] (223.7 KW)
dimensions :
wingspan : 14.36 [m], length : 8.99 [m], height : 3.3[m]
wing area : 50.2 [m^2]
weights :
max.take-off weight : 1984 [kg]
empty weight operational (estimation): 1150.0 [kg] useful load : 500 [kg]
performance :
maximum speed :139 [km/u] op 2000 [m]
cruise speed :125 [km/u] op 2000 [m]
service ceiling : 4500 [m]
range : 460 [km]
description :
2-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
engine, landing gear and useful load in or attached to fuselage, fuel in/on the wing
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.64 [ ]
estimated diameter airscrew 2.96 [m]
angle of attack prop : 13.57 [ ]
reduction : 1.00 [ ]
airscrew revs : 1650 [r.p.m.]
pitch at Max speed 1.40 [m]
blade-tip speed at Vmax and max revs. : 217 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.19 [m]
mean wing chord : 1.75 [m]
The 14T had the fuel tanks attached to the wings, giving more space for carrying passengers
calculated wing chord (rounded leading edge tips): 1.80 [m]
wing aspect ratio : 8.22 []
estimated gap : 1.69 [m]
gap/chord : 0.97 [ ]
seize (span*length*height) : 426 [m^3]
passenger seating pitch : 85 [cm]
passenger cabin width : 0.75 [m] cabin length : 1.70 [m]
luggage compartment: 1.92 [m3]
enough space for 319 [kg] luggage/freight
calculation : *2* (fuel consumption)
oil consumption : 4.7 [kg/hr]
fuel consumption(cruise speed) : 52.8 [kg/hr] (72.0 [litre/hr]) at 62 [%] power
distance flown for 1 kg fuel : 2.37 [km/kg] at 2250 [m] cruise height, sfc : 382.0
[kg/kwh]
estimated total fuel capacity : 300.59 [litre] (220.33 [kg])
calculation : *3* (weight)
weight engine(s) dry : 350.0 [kg] = 1.56 [kg/KW]
weight 28.7 litre oil tank : 2.44 [kg]
oil tank filled with 1.7 litre oil : 1.5 [kg]
oil in engine 8.7 litre oil : 7.8 [kg]
fuel in engine 1.5 litre fuel : 1.12 [kg]
weight 30.6 litre gravity patrol tank(s) : 4.6 [kg]
weight radiator : 32.1 [kg]
Breguet 14Tbis Sanitaire, flying ambulance
weight exhaust pipes & fuel lines 26.9 [kg]
weight self-starter : 5.5 [kg]
weight cowling 8.9 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 67.8 [kg]
total weight propulsion system : 506 [kg](25.5 [%])
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fuselage skeleton (wood gauge : 7.39 [cm]): 126 [kg]
bracing : 8.6 [kg]
fuselage covering ( 15.3 [m2] doped linen fabric) : 4.9 [kg]
weight instruments. : 1.1 [kg]
weight lighting : 1.1 [kg]
weight controls : 5.3 [kg]
weight seats : 3.0 [kg]
weight engine mounts & firewalls : 11 [kg]
total weight fuselage : 161 [kg](8.1 [%])
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weight wing covering (doped linen fabric) : 39 [kg]
total weight ribs (93 ribs) : 118 [kg]
weight fuel tanks empty for total 135 [litre] fuel : 11 [kg]
load on front upper spar (clmax) per running metre : 789.7 [N]
load on rear upper spar (vmax) per running metre : 389.2 [N]
total weight 8 spars : 111 [kg]
weight wings : 268 [kg]
weight wing/square meter : 5.34 [kg]
weight 8 interplane struts & cabane : 25.5 [kg]
weight cables (81 [m]) : 11.3 [kg] (= 140 [gram] per metre)
diameter cable : 4.8 [mm]
weight fin & rudder (2.4 [m2]) : 13.1 [kg]
weight stabilizer & elevator (5.6 [m2]): 30.5 [kg]
total weight wing surfaces & bracing : 359 [kg] (18.1 [%])
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Can only operate from paved runways
wheel pressure : 992.0 [kg]
weight 2 wheels (780 [mm] by 98 [mm]) : 39.6 [kg]
weight tailskid : 3.5 [kg]
weight undercarriage with axle 46.5 [kg]
total weight landing gear : 89.5 [kg] (4.5 [%]
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calculated empty weight : 1116 [kg](56.3 [%])
weight oil for 4.4 hours flying : 20.7 [kg]
weight cooling fluids : 48.3 [kg]
calculated operational weight empty : 1185 [kg] (59.7 [%])
estimated operational weight empty : 1150 [kg] (58.0 [%])
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weight crew : 81 [kg]
weight fuel for 1.0 hours flying : 53 [kg]
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operational weight : 1319 [kg](66.5 [%])
fuel reserve : 167.6 [kg] enough for 3.18 [hours] flying
possible additional useful load : 498 [kg]
operational weight fully loaded : 1984 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1984 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 8.87 [kg/kW]
power loading (operational without useful load) : 5.90 [kg/kW]
total power : 223.7 [kW] at 1650 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.3 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.5 [g]
design flight time : 2.94 [hours]
design cycles : 255 sorties, design hours : 750 [hours]
operational wing loading : 258 [N/m^2]
wing stress (3 g) during operation : 145 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.16 ["]
max. angle of attack (stalling angle) : 12.14 ["]
angle of attack at max. speed : 2.83 ["]
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 : 0.34 [ ]
induced drag coefficient at max. speed : 0.0081 [ ]
drag coefficient at max. speed : 0.0710 [ ]
drag coefficient (zero lift) : 0.0629 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 69 [km/u]
stalling speed at sea-level (MTOW): 85 [km/u]
landing speed at sea-level: 81 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 85 [km/hr] at 2250 [m] (power:32 [%])
min. power speed (max range) : 98 [km/hr] at 2250 [m] (power:36 [%])
max. rate of climb speed : 86.5 [km/hr] at sea-level
cruising speed : 125 [km/hr] op 2250 [m] (power:55 [%])
design speed prop : 132 [km/hr]
maximum speed : 139 [km/hr] op 2000 [m] (power:72 [%])
climbing speed at sea-level : 391 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 101.5 [km/u]
static prop wash : 114 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level : 173 [m]
lift/drag ratio : 7.60 [ ]
time to 2000m : 6.99 [min]
climb to 3000m : 12.12 [min]
published ceiling (4500 [m]
practical ceiling (operational weight) : 5273 [m] with flying weight :1319 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 3473 [m] with flying weight :1958 [kg]
max. dive speed : 285.8 [km/hr] at 2473 [m] height
turning speed at CLmax : 111.5 [km/u] at 50 [m] height
turn radius at 50m: 41 [m]
time needed for 360* turn 8.3 [seconds] at 50m
load factor at max. angle turn 2.60 ["g"]
calculation *10* (action radius & endurance)
published range : 460 [km] with 1 crew and 523.8 [kg] useful load and 88.1 [%] fuel
range : 516 [km] with 1 crew and 500.0 [kg] useful load and 98.9 [%] fuel
max range theoretically with additional fuel tanks for total 979.4 [litre] fuel : 1701.1 [km]
useful load with range 500km : 507 [kg]
production : 63.36 [tonkm/hour]
oil and fuel consumption per tonkm : 0.91 [kg]
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Literature :
Praktisch handbook vliegtuigen page 12
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
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(c) B van der Zalm 07 October 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4