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Sopwith Type 807Folder
role : light maritime two-seat patrol aircraft, ASW
first flight : 16 July 1914 (as landplane) operational : October 1914
country : United-Kingdom
design :
production : 13 aircraft at Kingston-on-Thames
general information :
Sopwith developed a race-airplane for the Circuit of Britain-race in 1914. After the first flight in July 1914 the wheel undercarriage was replaced by floats. This Seaplane had no folding wings, had equal span wings and stagger. See below three-side view :
The Circuit of Britain race was not held due to the outbreak of WWI.
From this race-Seaplane Sopwith developed a Seaplane for the RNAS with folding wings. The upper wing had a bigger span and it had no stagger. The folding wing was a novelty and it was patented by Sopwith.
(no stagger so it was more easy to make the wings fold). It was now indicated as Type 807 “Folder”.
The Folder was bought by the RNAS at the start of WWI and used for maritime patrol/reconnaissance. The RNAS took 12 Folders into service. Three Folders were carried on board the HMS Ark Royal and set off for the Dardanelles in February 1915. The Folder was one of the first aircraft to be used from ships by the RNAS. In operational use (scouting and artillery spotting) the seaplanes were underpowered and the floats to vulnerable to the seas.
First delivered to Calshot in January 1915, Sopwith 920 was immediately shipped to East Africa for use aboard HMS Kinsfauns Castle during the operation against the German cruiser Konigsberg.
Both 920 and 921 arrived in East Africa on 21 February 1915, where despite being adversely affected by the climate, they played a part in the ultimate destruction of the German cruiser, Konigsberg, on 11 July 1915. (> were able to take photographs of the German light cruiser)
No.920 at the shores of Niororo Island Februar 1915
users : RNAS
crew : 2
armament : no fixed armament
engine : 1 Gnome 9 Delta air-cooled 9 -cylinder atmospheric inlet-valve rotary engine 100 [hp](73.6 KW)
dimensions :
wingspan : 13.26 [m], length : 9.37 [m], height : 3.4[m]
wing area : 37.63 [m^2]
weights :
max.take-off weight : 1107 [kg]
empty weight operational : 717 [kg] bombload : 30 [kg]
performance :
maximum speed : 129 [km/hr] at sea-level
service ceiling : unknown
estimated endurance : 2.5 [hours]
estimated action radius : 145 [km]
description :
2-bay two float sesquiplane with tail float
no tip floats
upper wingtips supported by slanted flyingwires
two spar upper and lower wing
engines, landing gear, fuel and bombs in or attached to the fuselage
wings can be folded for easy storage
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.66 [ ]
(2.82 m) diameter two-bladed Chauviere propeller
estimated diameter airscrew 2.96 [m]
angle of attack prop : 14.41 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.79 [m]
blade-tip speed at Vmax and max revs. : 189 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.89 [m]
calculated wing chord (rounded tips): 2.17 [m]
wing aspect ratio : 7.01 []
estimated gap : 1.60 [m]
gap/chord : 0.85 [ ]
seize (span*length*height) : 422 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.3 [kg/hr]
fuel consumption(cruise speed) : 29.5 [kg/hr] (40.2 [litre/hr]) at 76 [%] power
distance flown for 1 kg fuel : 3.94 [km/kg]
estimated total fuel capacity : 114 [litre] (84 [kg])
calculation : *3* (weight)
weight engine(s) dry : 135.0 [kg] = 1.84 [kg/KW]
weight 23 litre oil tank : 1.9 [kg]
oil tank filled with 0.6 litre oil : 0.5 [kg]
oil in engine 0 litre oil : 0.4 [kg]
fuel in engine 1 litre fuel : 0.4 [kg]
weight 17 litre gravity patrol tank(s) : 2.6 [kg]
weight cowling 2.9 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 16.9 [kg]
total weight propulsion system : 159 [kg](14.3 [%])
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fuselage skeleton (wood gauge : 7.92 [cm]): 132 [kg]
bracing : 7.7 [kg]
fuselage covering ( 12.8 [m2] doped linen fabric) : 4.1 [kg]
weight controls + indicators: 6.5 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 2.1 [kg]
weight 97 [litre] main fuel tank empty : 7.8 [kg]
weight engine mounts & firewalls : 4 [kg]
total weight fuselage : 175 [kg](15.8 [%])
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weight wing covering (doped linen fabric) : 24 [kg]
total weight ribs (48 ribs) : 66 [kg]
load on front upper spar (clmax) per running metre : 822.5 [N]
load on rear upper spar (vmax) per running metre : 211.7 [N]
total weight 8 spars : 83 [kg]
weight wings : 173 [kg]
weight wing/square meter : 4.59 [kg]
weight wing folding system : 13 [kg]
weight 8 interplane struts & cabane : 21.2 [kg]
weight cables (61 [m]) : 7.9 [kg] (= 131 [gram] per metre)
diameter cable : 4.6 [mm]
weight fin & rudder (2.4 [m2]) : 11.6 [kg]
weight stabilizer & elevator (4.2 [m2]): 19.7 [kg]
total weight wing surfaces & bracing : 246 [kg] (22.2 [%])
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weight armament : 0 [kg]
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weight floats : 126 [kg] (11.4 [%])
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calculated empty weight : 707 [kg](63.8 [%])
weight oil for 3.0 hours flying : 18.8 [kg]
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calculated operational weight empty : 725 [kg] (65.5 [%])
published operational weight empty : 717 [kg] (64.8 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 59 [kg]
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operational weight : 946 [kg](85.5 [%])
bomb load : 30 [kg]
operational weight bombing mission : 976 [kg]
fuel reserve : 25 [kg] enough for 0.84 [hours] flying
possible additional useful load : 106 [kg]
operational weight fully loaded : 1107 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1107 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 12.87 [kg/kW]
total power : 73.6 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.1 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] loadfactor : 2.9 [g]
design flight time : 2.00 [hours]
design cycles : 725 sorties, design hours : 1450 [hours]
operational wing loading : 247 [N/m^2]
wing stress (3 g) during operation : 161 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.21 ["]
max.angle of attack (stalling angle) : 12.64 ["]
angle of attack at max.speed : 2.62 ["]
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 : 0.32 [ ]
induced drag coefficient at max.speed : 0.0061 [ ]
drag coefficient at max.speed : 0.0451 [ ]
drag coefficient (zero lift) : 0.0390 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 67 [km/u]
landing speed at sea-level (OW without bombload): 81 [km/hr]
min.drag speed (max endurance) : 85 [km/hr] at 1000 [m](power :49 [%])
min. power speed (max range) : 95 [km/hr] at 1000 [m] (power:53 [%])
max.rate of climb speed : 81.6 [km/hr] at sea-level
cruising speed : 116 [km/hr] op 1000 [m] (power:73 [%])
design speed prop : 123 [km/hr]
maximum speed : 129 [km/hr] op 100 [m] (power:98 [%])
climbing speed at sea-level (without bombload) : 145 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 198 [m]
lift/drag ratio : 10.29 [ ]
max. practical ceiling : 3400 [m] with flying weight :821 [kg]
practical ceiling (operational weight): 2750 [m] with flying weight :946 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2075 [m] with flying weight :1078 [kg]
published ceiling (0 [m]
climb to 1500m (without bombload) : 12.46 [min]
max.dive speed : 302.6 [km/hr] at 1075 [m] height
load factor at max.angle turn 1.72 ["g"]
turn radius at 500m: 46 [m]
time needed for 360* turn 11.6 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.84 [hours] with 2 crew and 136 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 2.50 [hours] with 2 crew and possible useful (bomb) load : 146 [kg] and 88.1 [%] fuel
action radius : 393 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 410 [litre] fuel : 1184 [km]
useful load with action-radius 250km : 174 [kg]
production : 20.17 [tonkm/hour]
oil and fuel consumption per tonkm : 1.77 [kg]
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Notes : fitted with a radiotransmitter ?
Literature :
Wikepedia
Warplanes of WOI page 8,38
They fought for the sky page 55
jagdflugzeuge WO I page 6
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 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4