Short S.63 s/n 81 being hoisted aboard cruiser HMS Hermes, note the hanging ailerons.
It was one of the first aircraft with folding wings for easy storage.
Short Type 81 (S.64) Folder
role : light maritime two-seat patrol aircraft, ASW
first flight : July 1913 operational : July 1913
country : United-Kingdom
design :
production : 9 aircraft s/n 81,82,89,90, 119-122, 186 at Eastchurch
general information :
The first of the Type 81 had the Shorts construction number S.63 and the Royal Navy serial number 81 and made its maiden flight in July 1913, piloted by Charles Rumney Samson.[2][3] The RNAS took delivery of 81 on 17 July 1913, and it was quickly deployed aboard the cruiser HMS Hermes, which had been converted to the first seaplane tender of the Royal Navy, for the 1913 Naval manoeuvres, where it was used for reconnaissance missions, using a radio set to report the position of shipping.[2] An engine failure on 1 August resulted in 81 ditching about 50 miles from Great Yarmouth, but although damaged, it was rescued by the German timber carrier Clara Mennig.[6][7] The second aircraft 82 took place in the unsuccessful search for the missing submarine HMS A7,[7] while four 160 hp Folders took part in the Spithead Fleet Review in July 1914.[8]The RNAS took delivery of the Sopwith Special floatplane which was specifically designed to drop a 14-inch torpedo in early July 1914, but it proved unable to take-off while carrying the planned weapon (or initially at all),[9] so Squadron-Commander Arthur Longmore, commander of the Calshot seaplane station which was carrying out the torpedo trials, suggested that one of the 160 hp Folders be modified for torpedo dropping. Drawings for torpedo gear was quickly produced by Shorts, and the aircraft, No. 121, flown by Longmore, carried out the first torpedo drop by a British aircraft on 28 July 1914.[10][11][nb 1][nb 2] Although several other 160 hp Folders were fitted with torpedo gear, the modification was of little practical use, as when carrying a torpedo, it could not carry an observer, and even with only 30 minutes fuel, was badly overloaded.[14]
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Following the outbreak of the First World War in August 1914, the Royal Navy purchased three fast cross-channel ferrys for use a seaplane carriers, one of which was HMS Engadine, to which three 160 hp folders were allocated. When Engadine took part in the Cuxhaven Raid on Christmas Day 1914, two of her Folders took off as part of the strike force, of which one returned to Engadine, and the other s/n 120 ditched near the Royal Navy submarine E11 at Norderney which recovered its crew.[3][15][16]Three 160 hp folders were sent to Durban in March 1915 to take part in operations against the German cruiser Königsberg, blockaded in the Rufiji Delta in German East Africa.(Tanzania) The Shorts struggled in the hot and humid conditions of East Africa, being unable to carry any bombload, but were used to carry out reconnaissance of the Königsberg before being replaced in June that year by a Caudron G.III and two Farman F.27s.[3][17]Source : wikepedia
users : RNAS
crew : 2
armament : no fixed armament
engine : 1 Gnome air-cooled 14 -cylinder atmospheric inlet-valve rotary engine 160
[hp](117.7 KW)
dimensions :
wingspan : 17.07 [m], length : 12.19 [m], height : 3.66[m]
wing area : 51.1 [m^2]
weights :
max.take-off weight : 1406 [kg]
empty weight operational : 909 [kg] bombload : 30 [kg]
performance :
maximum speed : 126 [km/hr] at sea-level
service ceiling : unknown
endurance : 5.0 [hours]
estimated action radius : 284 [km]
description :
2½-bay two float biplane with tail float
2 (aid) tip floats
upper wingtips supported by slanted struts
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 :0.65 [ ]
estimated diameter airscrew 3.55 [m]
angle of attack prop : 11.36 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1250 [r.p.m.]
pitch at Max speed 1.68 [m]
blade-tip speed at Vmax and max revs. : 235 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.71 [m]
calculated wing chord (rounded tips): 1.87 [m]
wing aspect ratio : 9.98 []
estimated gap : 1.88 [m]
gap/chord : 1.10 [ ]
seize (span*length*height) : 762 [m^3]
Folder s/n 120 took part in the Cuxhaven raid 25 December 1914 flown by Flt. Lt. A. J. Miley. Landed after the raid near Norderney. The crew was salvaged by submarine E11 and the aircraft was sunk to prevent it from getting in to German hands.
calculation : *2* (fuel consumption)
oil consumption : 11.8 [kg/hr]
fuel consumption(cruise speed) : 47.8 [kg/hr] (65.3 [litre/hr]) at 76 [%] power
distance flown for 1 kg fuel : 2.37 [km/kg]
estimated total fuel capacity : 370 [litre] (272 [kg])
calculation : *3* (weight)
weight engine(s) dry : 205.9 [kg] = 1.75 [kg/KW]
weight 82 litre oil tank : 6.9 [kg]
oil tank filled with 0.9 litre oil : 0.8 [kg]
oil in engine 1 litre oil : 0.6 [kg]
fuel in engine 1 litre fuel : 0.6 [kg]
weight 28 litre gravity patrol tank(s) : 4.2 [kg]
weight cowling 4.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 236 [kg](16.8 [%])
***************************************************************
fuselage skeleton (wood gauge : 7.33 [cm]): 147 [kg]
bracing : 11.2 [kg]
fuselage covering ( 21.7 [m2] doped linen fabric) : 7.0 [kg]
weight controls + indicators: 7.6 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 2.1 [kg]
weight 343 [litre] main fuel tank empty : 27.4 [kg]
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 220 [kg](15.6 [%])
***************************************************************
weight wing covering (doped linen fabric) : 33 [kg]
total weight ribs (67 ribs) : 84 [kg]
load on front upper spar (clmax) per running metre : 569.6 [N]
load on rear upper spar (vmax) per running metre : 217.6 [N]
total weight 8 spars : 95 [kg]
weight wings : 211 [kg]
weight wing/square meter : 4.14 [kg]
weight wing folding system : 16 [kg]
weight 12 interplane struts & cabane : 52.5 [kg]
weight cables (82 [m]) : 12.3 [kg] (= 150 [gram] per metre)
diameter cable : 4.9 [mm]
weight fin & rudder (4.1 [m2]) : 17.4 [kg]
weight stabilizer & elevator (5.7 [m2]): 24.2 [kg]
total weight wing surfaces & bracing : 334 [kg] (23.7 [%])
Folder s/n 119 flown by Flt. Cdr. R. P. Ross took also part in the Cuxhaven raid and returned safely to its carrier ship
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weight armament : 0 [kg]
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weight floats : 101 [kg] (7.2 [%])
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calculated empty weight : 890 [kg](63.3 [%])
weight oil for 6.0 hours flying : 70.6 [kg]
*******************************************************************
calculated operational weight empty : 960 [kg] (68.3 [%])
published operational weight empty : 909 [kg] (64.7 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 96 [kg]
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operational weight : 1218 [kg](86.6 [%])
bomb load : 30 [kg]
operational weight bombing mission : 1248 [kg]
fuel reserve : 158 [kg] enough for 3.30 [hours] flying
operational weight fully loaded : 1406 [kg] with fuel tank filled for 93 [%]
published maximum take-off weight : 1406 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 10.35 [kg/kW]
total power : 117.7 [kW] at 1250 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.0 [g] at 1000 [m]
limit load : 3.5 [g] ultimate load : 5.2 [g] load factor : 2.0 [g]
design flight time : 3.50 [hours]
design cycles : 286 sorties, design hours : 1000 [hours]
operational wing loading : 234 [N/m^2]
wing stress (3 g) during operation : 170 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.11 ["]
max.angle of attack (stalling angle) : 11.40 ["]
angle of attack at max.speed : 2.39 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.12 [ ]
lift coefficient at max.speed : 0.31 [ ]
induced drag coefficient at max.speed : 0.0042 [ ]
drag coefficient at max.speed : 0.0567 [ ]
drag coefficient (zero lift) : 0.0525 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 66 [km/u]
landing speed at sea-level (OW without bombload): 80 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 77 [km/hr] at 1000 [m] (power:37 [%])
min. power speed (max range) : 77 [km/hr] at 1000 [m] (power:37 [%])
max.rate of climb speed : 75.3 [km/hr] at sea-level
cruising speed : 113 [km/hr] op 1000 [m] (power:70 [%])
design speed prop : 120 [km/hr]
maximum speed : 126 [km/hr] op 100 [m] (power:98 [%])
climbing speed at sea-level (without bombload) : 210 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 92 [m]
lift/drag ratio : 10.58 [ ]
max. practical ceiling : 4600 [m] with flying weight :1065 [kg]
practical ceiling (operational weight): 4050 [m] with flying weight :1218 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 3550 [m] with flying weight :1358 [kg]
published ceiling (0 [m]
climb to 1500m (without bombload) : 8.14 [min]
climb to 3000m (without bombload) : 21.24 [min]
max.dive speed : 273.6 [km/hr] at 2550 [m] height
load factor at max.angle turn 2.19 ["g"]
turn radius at 500m: 41 [m]
time needed for 360* turn 9.2 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 5.51 [hours] with 2 crew and 20 [kg] useful load and 97.1 [%] fuel
published endurance : 5.00 [hours] with 2 crew and possible useful (bomb) load : 44 [kg] and 88.1 [%] fuel
action radius : 312 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 497 [litre] fuel : 864 [km]
useful load with action-radius 250km : 154 [kg]
production : 17.43 [tonkm/hour]
oil and fuel consumption per tonkm : 3.42 [kg]
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Literature :
Jane’s fighting aircraft WOI page 78, 79f (s/n 121)
Historische vliegtuigen page73
Warplanes page 29,38
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