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Sopwith type 9700 1˝-Strutter
role : light bomber
first flight : operational : July 1916
country : United-Kingdom
design :
production : 5939 aircraft
general information :
The type 9400 was converted to a single-seater (type 9700) where the observer's place was covered and replaced with a rack for 4 bombs of 29.5 kg. With this bomb load it had a good range. It could be deployed as the 1e Real strategic bomber. The RFC engaged the first 1˝-Strutters in the summer of 1916 during the Battle of the Somme.
The Strutters suffered heavy losses in April 1917, "Bloody April". In the single-seat bomber version, the moveable machine gun was removed, making it very vulnerable to attacks from behind. The French also made a lot of use of the tyoe, referred to as 1B1.
De Strutters were intended to operate in flights of seven. The 5 lead aircraft were single-seater bombers and the two in the rear would be two-seaters acting as fighter escort.
users : France, RFC
crew : 1
armament : 1 synchronized 7.70 [mm] (0.303 in) Vickers machine-gun
engine : 1 Clerget 9B air-cooled 9 -cylinder two-valve rotary engine 130 [hp](95.6 KW)
dimensions :
wingspan : 10.21 [m], length : 7.7 [m], height : 3.12[m]
wing area : 32.14 [m^2]
weights :
max.take-off weight : 977 [kg]
empty weight operational : 593 [kg] bombload : 118 [kg]
performance :
maximum speed : 160 [km/u] op 1981 [m]
service ceiling : 3962 [m]
endurance : 4.0 [hours]
estimated action radius : 288 [km]
description :
1-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
engines, landing gear, fuel and bombs in or attached to the fuselage
French 1B1
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.66 [ ]
estimated diameter airscrew 2.80 [m]
angle of attack prop : 17.92 [ ]
reduction : 1.00 [ ]
airscrew revs : 1250 [r.p.m.]
pitch at Max speed 2.13 [m]
blade-tip speed at Vmax and max revs. : 189 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.57 [m]
calculated wing chord (rounded tips): 1.77 [m]
wing aspect ratio : 6.49 []
estimated gap : 1.50 [m]
gap/chord : 0.95 [ ]
seize (span*length*height) : 245 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.0 [kg/hr]
fuel consumption(cruise speed) : 30.3 [kg/hr] (41.3 [litre/hr]) at 69 [%] power
In this painting the French 1B1 carried a machine gun on the upper wing.
distance flown for 1 kg fuel : 4.76 [km/kg]
estimated total fuel capacity : 187 [litre] (137 [kg])
calculation : *3* (weight)
weight engine(s) dry : 173.0 [kg] = 1.81 [kg/KW]
weight 35 litre oil tank : 2.9 [kg]
oil tank filled with 0.7 litre oil : 0.6 [kg]
oil in engine 1 litre oil : 0.5 [kg]
fuel in engine 1 litre fuel : 0.5 [kg]
weight 18 litre gravity patrol tank(s) : 2.6 [kg]
weight cowling 3.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 200 [kg](20.5 [%])
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fuselage skeleton (wood gauge : 6.38 [cm]): 80 [kg]
bracing : 4.4 [kg]
fuselage covering ( 11.2 [m2] doped linen fabric) : 3.6 [kg]
weight controls + indicators: 5.9 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 8.3 [kg]
weight bomb sight : 1.0 [kg]
weight 170 [litre] main fuel tank empty : 13.6 [kg]
weight engine mounts & firewalls : 5 [kg]
total weight fuselage : 130 [kg](13.3 [%])
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weight wing covering (doped linen fabric) : 21 [kg]
total weight ribs (51 ribs) : 58 [kg]
load on front upper spar (clmax) per running metre : 755.7 [N]
load on rear upper spar (vmax) per running metre : 264.5 [N]
total weight 8 spars : 45 [kg]
weight wings : 124 [kg]
weight wing/square meter : 3.85 [kg]
weight 4 interplane struts & cabane : 11.6 [kg]
weight cables (50 [m]) : 3.6 [kg] (= 71 [gram] per metre)
diameter cable : 3.4 [mm]
weight fin & rudder (1.2 [m2]) : 4.8 [kg]
weight stabilizer & elevator (3.6 [m2]): 14.2 [kg]
total weight wing surfaces & bracing : 158 [kg] (16.2 [%])
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weight machine-gun(s) : 15.9 [kg]
weight ammunition magazine(s) :1.8 [kg]
weight synchronizing system : 1.0 [kg]
weight armament : 19 [kg]
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wheel pressure : 488.5 [kg]
weight 2 wheels (730 [mm] by 81 [mm]) : 24.7 [kg]
weight tailskid : 2.4 [kg]
weight undercarriage with axle 29.9 [kg]
total weight landing gear : 56.9 [kg] (5.8 [%]
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French 1B1
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calculated empty weight : 563 [kg](57.7 [%])
weight oil for 4.8 hours flying : 28.9 [kg]
weight ammunition (400 rounds) : 13.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
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calculated operational weight empty : 607 [kg] (62.1 [%])
published operational weight empty : 593 [kg] (60.7 [%])
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weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 61 [kg]
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operational weight : 749 [kg](76.6 [%])
bomb load : 118 [kg]
operational weight bombing mission : 867 [kg]
fuel reserve : 77 [kg] enough for 2.54 [hours] flying
possible additional useful load : 34 [kg]
operational weight fully loaded : 977 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 977 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 10.22 [kg/kW]
total power : 95.6 [kW] at 1250 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.0 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.1 [g]
design flight time : 3.20 [hours]
design cycles : 484 sorties, design hours : 1550 [hours]
wing loading (MTOW) : 298 [N/m^2]
wing stress (3 g) during operation : 206 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.48 ["]
max. angle of attack (stalling angle) : 12.60 ["]
angle of attack at max. speed : 1.35 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.12 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
lift coefficient at max. speed : 0.23 [ ]
induced drag coefficient at max. speed : 0.0046 [ ]
drag coefficient at max. speed : 0.0340 [ ]
drag coefficient (zero lift) : 0.0294 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 65 [km/u]
landing speed at sea-level (OW without bombload): 78 [km/hr]
min. drag speed (max endurance) : 101 [km/hr] at 1981 [m](power :37 [%])
min. power speed (max range) : 106 [km/hr] at 1981 [m] (power:38 [%])
max. rate of climb speed : 100.0 [km/hr] at sea-level
cruising speed : 144 [km/hr] op 1981 [m] (power:60 [%])
design speed prop : 152 [km/hr]
maximum speed : 160 [km/hr] op 1981 [m] (power:76 [%])
climbing speed at sea-level (without bombload) : 286 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 163 [m]
lift/drag ratio : 9.88 [ ]
max. practical ceiling : 5625 [m] with flying weight :688 [kg]
practical ceiling (operational weight): 5150 [m] with flying weight :749 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 3725 [m] with flying weight :947 [kg]
published ceiling (3962 [m]
climb to 1500m (without bombload) : 5.83 [min]
climb to 3000m (without bombload) : 14.27 [min]
max. dive speed : 383.7 [km/hr] at 2725 [m] height
load factor at max. angle turn 1.81 ["g"]
turn radius at 500m: 49 [m]
time needed for 360* turn 11.4 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 4.54 [hours] with 1 crew and 152 [kg] bombload and 100.0 [%] fuel
published endurance : 4.00 [hours] with 1 crew and possible useful (bomb) load : 168 [kg] and 88.1 [%] fuel
action radius : 640 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 414 [litre] fuel : 1445 [km]
useful load with action-radius 250km : 184 [kg]
production : 26.47 [tonkm/hour]
oil and fuel consumption per tonkm : 1.37 [kg]
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Literature :
Bombers 1914-19 page 60,138
Praktisch handboek vliegtuigen deel 1 page 60,182
Wikipedia
Warplanes WOI page70,95,96
Jane’s FAWOI page 83f
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.
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(c) B van der Zalm 21 August 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4