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weight and performance calculations for the Bleriot SPAD 46
Bleriot SPAD 46
role : light passenger aircraft
importance : ****
first flight : operational : February 1922
country : France
design :
production : 40 aircraft
general information :
Developed from it’s predecessor the SPAD S.33. It had a bigger span and a more powerful engine. In the closed cabin it had space for 4 passengers, occasionally a 5 th passenger was seated beside the pilot in an open cockpit.
users : Franco-Roumaine (38), CIDNA
crew : 1 passengers : 5
engine : 1 Lorraine-Dietrich 12Da liquid-cooled 12 -cylinder V-engine 370 [hp](275.9 KW)
dimensions :
wingspan : 12.6 [m], length : 9.05 [m], height : 3.18[m]
wing area : 47.0 [m^2]
weights :
max.take-off weight : 2270 [kg]
empty weight operational : 1417 [kg] useful load : 500 [kg]
performance :
maximum speed :214 [km/hr] at sea-level
cruise speed :193 [km/u] op 100 [m]
service ceiling : 5050 [m]
range : 800 [km]
description :
1-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 :0.65 [ ]
estimated diameter airscrew 3.10 [m]
angle of attack prop : 19.55 [ ]
reduction : 1.00 [ ]
airscrew revs : 1650 [r.p.m.]
pitch at Max speed 2.16 [m]
blade-tip speed at Vmax and max revs. : 231 [m/s]
calculation : *1* (dimensions)
wing chord : 1.99 [m]
mean wing chord : 1.87 [m]
calculated wing chord (rounded leading edge tips): 1.93 [m]
wing aspect ratio : 6.76 []
estimated gap : 1.80 [m]
gap/chord : 0.97 [ ]
seize (span*length*height) : 363 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 5.0 [kg/hr]
fuel consumption(cruise speed) : 57.5 [kg/hr] (78.5 [litre/hr]) at 63 [%] power
distance flown for 1 kg fuel : 3.35 [km/kg] at 2525 [m] cruise height, sfc : 330.1 [kg/kwh]
estimated total fuel capacity : 370.01 [litre] (271.22 [kg])
calculation : *3* (weight)
weight engine(s) dry : 420.0 [kg] = 1.52 [kg/KW]
weight 34.5 litre oil tank : 2.93 [kg]
oil tank filled with 2.1 litre oil : 1.9 [kg]
oil in engine 10.8 litre oil : 9.7 [kg]
fuel in engine 1.9 litre fuel : 1.38 [kg]
weight 33.4 litre gravity patrol tank(s) : 5.0 [kg]
weight radiator : 39.5 [kg]
weight exhaust pipes & fuel lines 33.1 [kg]
weight self-starter : 6.8 [kg]
weight cowling 11.0 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 86.5 [kg]
total weight propulsion system : 615 [kg](27.1 [%])
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fuselage skeleton (wood gauge : 8.31 [cm]): 160 [kg]
fuselage width : 1.40 [m]
cabin layout : pitch : 87 [cm] (1+1) seating in 2.5 rows
passenger cabin area : 2.68 [m2]
weight 5.0 windows : 4.50 [kg]
passenger cabin width : 1.23 [m] cabin length : 2.17 [m] cabin height : 1.90 [m]
cabin space : 5.10 [m3]
weight cabin furbishing : 23.70 [kg]
bracing : 10.2 [kg]
fuselage covering ( 15.5 [m2] doped linen fabric) : 4.7 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 5.1 [kg]
weight seats : 30.0 [kg]
weight 337 [litre] main fuel tank empty : 26.9 [kg]
weight air conditioning : 8 [kg]
weight engine mounts & firewalls : 14 [kg]
total weight fuselage : 290 [kg](12.8 [%])
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weight wing covering (doped linen fabric) : 39 [kg]
total weight ribs (99 ribs) : 135 [kg]
load on front upper spar (clmax) per running metre : 1057.0 [N]
load on rear upper spar (vmax) per running metre : 507.4 [N]
total weight 8 spars : 96 [kg]
weight wings : 270 [kg]
weight wing/square meter : 5.75 [kg]
weight 4 interplane struts & cabane : 26.2 [kg]
weight cables (62 [m]) : 9.3 [kg] (= 152 [gram] per metre)
diameter cable : 5.0 [mm]
weight fin & rudder (1.8 [m2]) : 10.9 [kg]
weight stabilizer & elevator (5.3 [m2]): 30.7 [kg]
total weight wing surfaces & bracing : 347 [kg] (15.3 [%])
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wheel pressure : 1135.0 [kg]
weight 2 wheels (810 [mm] by 125 [mm]) : 49.7 [kg]
weight tailskid : 4.1 [kg]
weight undercarriage with axle 48.5 [kg]
total weight landing gear : 102.2 [kg] (4.5 [%]
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calculated empty weight : 1354 [kg](59.7 [%])
weight oil for 5.0 hours flying : 24.8 [kg]
weight cooling fluids : 59.6 [kg]
calculated operational weight empty : 1439 [kg] (63.4 [%])
published operational weight empty : 1417 [kg] (62.4 [%])
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weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 115 [kg]
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operational weight empty: 1635 [kg](72.0 [%])
weight 5 passengers : 385 [kg]
weight luggage & freight : 115 [kg]
operational weight loaded: 2135 [kg](72.0 [%])
fuel reserve : 135.4 [kg] enough for 2.35 [hours] flying
operational weight fully loaded : 2270 [kg] with fuel tank filled for 92 [%]
published maximum take-off weight : 2270 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 8.23 [kg/kW]
power loading (operational without useful load) : 5.92 [kg/kW]
total power : 275.9 [kW] at 1650 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 4.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 3.32 [hours]
design cycles : 1011 sorties, design hours : 3360 [hours]
operational wing loading : 341 [N/m^2]
wing stress (3 g) during operation : 178 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.22 ["]
max. angle of attack (stalling angle) : 12.74 ["]
angle of attack at max. speed : 0.72 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
lift coefficient at max. speed : 0.16 [ ]
induced drag coefficient at max. speed : 0.0021 [ ]
drag coefficient at max. speed : 0.0296 [ ]
drag coefficient (zero lift) : 0.0275 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 79 [km/u]
stalling speed at sea-level (MTOW): 94 [km/u]
landing speed at sea-level: 93 [km/hr]
min. drag speed (max endurance) : 127 [km/hr] at 2525 [m](power :35 [%])
min. power speed (max range) : 133 [km/hr] at 2525 [m] (power:36 [%])
max. rate of climb speed : 127.4 [km/hr] at sea-level
cruising speed : 193 [km/hr] op 2525 [m] (power:63 [%])
design speed prop : 203 [km/hr]
maximum speed : 214 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level : 370 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 112.3 [km/u]
emergency/TO power : 400 [hp] at 1920 [rpm]
static prop wash : 134 [km/u]
take-off distance at sea-level : 167 [m]
lift/drag ratio : 10.41 [ ]
climb to 1000m with max payload : 5.63 [min]
climb to 2000m with max payload : 13.85 [min]
climb to 3000m with max payload : 25.56 [min]
published ceiling (5050 [m]
practical ceiling (operational weight) : 5978 [m] with flying weight :1635 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 4188 [m] with flying weight :2241 [kg]
max. dive speed : 465.9 [km/hr] at 3188 [m] height
turning speed at CLmax : 121.5 [km/u] at 50 [m] height
turn radius at 50m: 55 [m]
time needed for 360* turn 10.3 [seconds] at 50m
load factor at max. angle turn 2.33 ["g"]
calculation *10* (action radius & endurance)
published range : 800 [km] with 1 crew and 511.5 [kg] useful load and 88.1 [%] fuel
range : 838 [km] with 1 crew and 500.0 [kg] useful load and 92.3 [%] fuel
max range theoretically with additional fuel tanks for total 1023.8 [litre] fuel : 2512.3 [km]
useful load with range 500km : 601 [kg]
production : 115.77 [tonkm/hour]
oil and fuel consumption per tonkm : 0.54 [kg]
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Fatal Crashes :
27 August 1923 F-AEGN of Franco – Roumaine crashed on landing at Bucharest, Romania. Pilot & passenger killed in the crash.
Crashed F-AEBK, (SPAD S.66) of CIDNA, 5 June 1928 engine failure while flying at 50m height, stalled during emergency landing. Crashed in open field in Kralovec, Czech republic. Radio-navigator Franz Przybiski killed, pilot injured. Pilot : Frantisek Lehky. Flight from Prague to Warsaw.
In 1925, the surviving 34 Franco-Roumaine aircraft were recalled to Blériot where they underwent remanufacture to incorporate various refinements. These refurbished aircraft were redesignated S.66 .
Literature :
Praktisch handboek vliegtuigen deel 2
CIDNA (aerobernie.bplaced.net)
Civil Aircraft Register - France (airhistory.org.uk)
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 01 January 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4