Type 74 s/n 77
Short Admiralty Type 74
role : light maritime two-seat patrol aircraft, ASW
first flight : 4 January 1914 operational : March 1914
country : United-Kingdom
design : Horace Short
production : 7 aircraft navy s/n 74 to 80, 180, 182, 183
general information :
general information : float plane operating from coastal stations. Wings could not be
folded. For ship-born operations a few aircraft were built with folding wings, these were
known as “improved” type 74 and received Navy s/n 811 – 818. 4 of these took part in the Cuxhaven Christmas raid* Launched from 3 ships 7 Short float planes took of to destroy zeppelins at there base in Nordholz on 25 December 1914. The formation was made out of 4 improved type 74’s (s/n 811,814,815), 2 type 81 s/n 119 and 120 and 2 type 135 s/n 135 and 136.
All carried three 20 lb bombs
Due to bad weather they were unable to find there target and instead bombed some
other military objects with little damage.
The crews of all seven aircraft survived the raid, having been airborne for over three
hours.[6] Short 'Improved Type 74' (RNAS serial no. 811 was flown by Flt. Lt. Charles Edmonds. In august 1915 Edwonds will be the first to sink a ship with a air-launched
torpedo from a Short 184 for the Turkish coast.
The Cuxhaven raid was the first combined sea and air strike which was executed by the
Royal Navy.
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 : 17.35 [m], length : 11.9 [m], height : 3.6[m]
wing area : 54.0 [m^2]
weights :
max.take-off weight : 1225 [kg]
empty weight operational (estimation): 750.0 [kg] bombload : 30 [kg]
performance :
maximum speed : 105 [km/hr] at sea-level
service ceiling : unknown
estimated action radius : 300 [km]
Impression of the raid on Cuxhaven, 25 December 1914. Improved type 74 s/n 815
description :
3˝-bay two float biplane with tail float
2 (aid) tip floats
upper wingtips supported by slanted struts
two spar upper and lower wing
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.66 [ ]
estimated diameter airscrew 2.80 [m]
angle of attack prop : 12.47 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.46 [m]
blade-tip speed at Vmax and max revs. : 178 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.73 [m]
calculated wing chord (rounded tips): 1.88 [m]
wing aspect ratio : 10.03 []
estimated gap : 1.89 [m]
gap/chord : 1.09 [ ]
seize (span*length*height) : 743 [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 : 3.20 [km/kg]
estimated total fuel capacity : 290 [litre] (212 [kg])
calculation : *3* (weight)
weight engine(s) dry : 135.0 [kg] = 1.84 [kg/KW]
weight 55 litre oil tank : 4.7 [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](13.0 [%])
***************************************************************
fuselage skeleton (wood gauge : 7.02 [cm]): 132 [kg]
bracing : 9.8 [kg]
fuselage covering ( 20.7 [m2] doped linen fabric) : 6.6 [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 273 [litre] main fuel tank empty : 21.8 [kg]
weight engine mounts & firewalls : 4 [kg]
total weight fuselage : 195 [kg](15.9 [%])
***************************************************************
weight wing covering (doped linen fabric) : 35 [kg]
total weight ribs (58 ribs) : 73 [kg]
load on front upper spar (clmax) per running metre : 498.9 [N]
load on rear upper spar (vmax) per running metre : 180.9 [N]
total weight 8 spars : 86 [kg]
weight wings : 193 [kg]
weight wing/square meter : 3.58 [kg]
weight 16 interplane struts & cabana : 49.6 [kg]
weight cables (106 [m]) : 14.3 [kg] (= 136 [gram] per metre)
diameter cable : 4.7 [mm]
weight fin & rudder (4.2 [m2]) : 15.6 [kg]
weight stabilizer & elevator (6.1 [m2]): 22.2 [kg]
total weight wing surfaces & bracing : 295 [kg] (24.1 [%])
*******************************************************************
weight armament : 0 [kg]
********************************************************************
weight floats : 87 [kg] (7.1 [%])
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********************************************************************
calculated empty weight : 736 [kg](60.1 [%])
weight oil for 7.6 hours flying : 47.6 [kg]
*******************************************************************
calculated operational weight empty : 783 [kg] (63.9 [%])
estimated operational weight empty : 750 [kg] (61.2 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 59 [kg]
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operational weight : 1004 [kg](82.0 [%])
bomb load : 30 [kg]
operational weight bombing mission : 1034 [kg]
fuel reserve : 154 [kg] enough for 5.21 [hours] flying
possible additional useful load : 37 [kg]
operational weight fully loaded : 1225 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1225 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 13.65 [kg/kW]
total power : 73.6 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.8 [g] at 1000 [m]
limit load : 3.5 [g] ultimate load : 5.2 [g] load factor : 2.1 [g]
design flight time : 4.44 [hours]
design cycles : 281 sorties, design hours : 1250 [hours]
operational wing loading : 182 [N/m^2]
wing stress (3 g) during operation : 153 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.11 ["]
max.angle of attack (stalling angle) : 11.37 ["]
angle of attack at max.speed : 2.82 ["]
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 : 0.35 [ ]
induced drag coefficient at max.speed : 0.0053 [ ]
drag coefficient at max.speed : 0.0582 [ ]
drag coefficient (zero lift) : 0.0530 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 59 [km/u]
landing speed at sea-level (OW without bombload): 70 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 68 [km/hr] at 1000 [m] (power:41 [%])
min. power speed (max range) : 68 [km/hr] at 1000 [m] (power:41 [%])
max.rate of climb speed : 63.8 [km/hr] at sea-level
cruising speed : 94 [km/hr] op 1000 [m] (power:71 [%])
design speed prop : 100 [km/hr]
maximum speed : 105 [km/hr] op 100 [m] (power:98 [%])
climbing speed at sea-level (without bombload) : 154 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 152 [m]
lift/drag ratio : 10.56 [ ]
max. practical ceiling : 3900 [m] with flying weight :879 [kg]
practical ceiling (operational weight): 3350 [m] with flying weight :1004 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2500 [m] with flying weight :1196 [kg]
published ceiling (0 [m]
climb to 1500m (without bombload) : 11.33 [min]
max.dive speed : 251.8 [km/hr] at 1500 [m] height
load factor at max.angle turn 1.98 ["g"]
turn radius at 500m: 33 [m]
time needed for 360* turn 8.8 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 7.21 [hours] with 2 crew and 67 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 6.35 [hours] with 2 crew and possible useful (bomb) load : 93 [kg] and 88.1 [%] fuel
action radius : 416 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 492 [litre] fuel : 1156 [km]
useful load with action-radius 250km : 205 [kg]
production : 19.35 [tonkm/hour]
oil and fuel consumption per tonkm : 1.85 [kg]
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Literature : Wikepedia
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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