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weight and performance calculations for the Cody British Army Aeroplane nr.I
Cody British Army Aeroplane nr.I
role : experimental/research/flying trials
importance : ****
first flight : 16 October 1908 operational : October 1908
country : United-Kingdom
design : Samuel Franklin Cody
production : 1 prototype
general information :
Cody built this biplane in 1908 at the Army Balloon Factory at Farnborough. It made the first sustained powered flight in the UK on 16 October 1908. A distance of 424m was covered but when it made a turn to avoid some trees a wingtip touched the ground. The resulting crash caused substantial damage. The rest of the year it took Cody to repair the aircraft and make major modifications. The gap between the wings was increased from 2.44m to 2.74m. The big and heavy, strongly built aircraft could only just stay in the air. In January 1909 flying trials started again. On 20 January, a flight of 370m was made, reaching a height of 8m. But again, it crashed when making a turn. In February more successful flights were made. But then the army stopped the funding and Cody had to continue at his own expense, but he could keep the aircraft. On 14 May 1909 Cody made a flight of over a mile between Laffan’s plain and Danger Hill (ca.51°16’17”N, 46°08”25’O Farnborough airfield) . The tail wheel was now replaced by a skid. On 21 July 1909 he made a circular flight of 4 miles (6.4 km). The next modification was to replace the engine with a 60 hp ENV type F and to switch the position for the pilot, now sitting in front of the engine. On 14 August 1909 he took his wife as passenger on a 3-mile flight. With a passenger it could just take-off, with TOW of 1245 kg, empty weight ca. 1065 kg. take-off run 200m, max ceiling 113m. On 8 September 1909 he made a flight of over an hour above Laffan’s Plain, flying 64km before his fuel ran out.
users : Samuel Franklin Cody
crew : 1
engine : 1 Antoinette 50hp liquid-cooled 8 -cylinder V-engine 50 [hp](37.3 KW)
dimensions :
wingspan : 15.85 [m], length : 13.41 [m], height : 3.96[m]
wing area : 73.39 [m^2]
weights :
max.take-off weight : 1152 [kg]
empty weight operational : 1025 [kg] useful load : 0 [kg]
performance :
maximum speed :64 [km/hr] at sea-level
cruise speed :58 [km/u] op 50 [m]
service ceiling : 500 [m]
range : 20 [km]
estimated endurance : 0.35 [hours]
Samuel F Cody (wearing a white coat) walks away from the wreckage of British Army Aircraft I shortly after crashing on Laffan's Plain, near Aldershot after making what was to be recognised as the first sustained powered flight in Britain.
description :
3-bay biplane with fixed landing gear with nosewheel and tail wheel
two spar upper and lower wings
canard wing
engine, landing gear and useful load in or attached to fuselage, fuel in gravity tank
airscrew :
two fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.63 [ ]
estimated diameter airscrew 2.08 [m]
angle of attack prop : 11.19 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1100 [r.p.m.]
pitch at Max speed 0.97 [m]
blade-tip speed at Vmax and max revs. : 121 [m/s]
calculation : *1* (dimensions)
wing chord : 2.28 [m]
mean wing chord : 2.32 [m]
calculated wing chord (rounded leading edge tips): 2.38 [m]
wing aspect ratio : 6.85 []
gap : 2.44 [m]
gap/chord : 1.05 [ ]
seize (span*length*height) : 842 [m^3]
Samuel Cody in his Army Aeroplane nr.I with 50hp Antoinette engine
calculation : *2* (fuel consumption)
oil consumption : 0.9 [kg/hr]
fuel consumption(cruise speed) : 21.0 [kg/hr] (28.6 [litre/hr]) at 96 [%] power
distance flown for 1 kg fuel : 2.74 [km/kg] at 250 [m] cruise height, sfc : 587.5 [kg/kwh]
estimated total fuel capacity : 9.94 [litre] (7.29 [kg])
calculation : *3* (weight)
weight engine(s) dry : 95.0 [kg] = 2.55 [kg/KW]
weight transmission & gear (engines in fuselage) : 14.9 [kg]
weight 1.4 litre oil tank : 0.12 [kg]
oil tank filled with 0.3 litre oil : 0.3 [kg]
oil in engine 2.1 litre oil : 1.9 [kg]
fuel in engine 0.3 litre fuel : 0.19 [kg]
weight 9.9 litre gravity patrol tank(s) : 1.5 [kg]
weight radiator : 5.3 [kg]
weight exhaust pipes & fuel lines 4.2 [kg]
weight cowling 1.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 10.6 [kg]
total weight propulsion system : 135 [kg](11.8 [%])
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fuselage skeleton (wood gauge : 8.89 [cm]): 271 [kg]
bracing : 21.4 [kg]
weight instruments. : 1.1 [kg]
weight controls : 6.6 [kg]
weight seats : 3.0 [kg]
weight engine mount : 1.9 [kg]
total weight fuselage : 305 [kg](26.5 [%])
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weight wing covering (doped linen fabric) : 82 [kg]
total weight ribs (41 ribs) : 68 [kg]
load on front upper spar (clmax) per running metre : 831.0 [N]
total weight 8 spars : 120 [kg]
weight wings : 270 [kg]
weight wing/square meter : 3.68 [kg]
weight 12 interplane struts & cabane : 97.6 [kg]
weight cables (122 [m]) : 23.0 [kg] (= 188 [gram] per metre)
diameter cable : 5.5 [mm]
weight fin & rudder (2.9 [m2]) : 11.2 [kg]
weight stabilizer & elevator (8.3 [m2]): 30.9 [kg]
total weight wing surfaces & bracing : 433 [kg] (37.6 [%])
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good soft ground capabilities
wheel pressure : 506.9 [kg]
weight 3 wheels (850 [mm] by 131 [mm]) : 42.7 [kg]
weight tailskid : 5.2 [kg]
weight undercarriage with axle 100.0 [kg]
total weight landing gear : 147.8 [kg] (12.8 [%]
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In above drawing the pilot now is sitting in front of the engine, also there is provision for taking a passenger. Gap 7 ft 6 in = 2.28 m Span : 52ft = 15.85m wing area 780 sq.ft = 72.46m2 Gap : 9 ft = 2.74m
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calculated empty weight : 1021 [kg](88.6 [%])
weight oil for 0.4 hours flying : 0.4 [kg]
weight cooling fluids : 8.1 [kg]
calculated operational weight empty : 1030 [kg] (89.4 [%])
published operational weight empty : 1025 [kg] (89.0 [%])
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weight crew : 81 [kg]
weight fuel for 0.3 hours flying : 7 [kg]
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operational weight : 1118 [kg](97.0 [%])
fuel reserve : 0.4 [kg] enough for 0.02 [hours] flying
possible additional useful load : 34 [kg]
operational weight fully loaded : 1152 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1152 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 30.90 [kg/kW]
power loading (operational without useful load) : 29.97 [kg/kW]
total power : 37.3 [kW] at 1100 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 3.9 [g]
design flight time : 0.28 [hours]
design cycles : 1830 sorties, design hours : 152 [hours]
operational wing loading : 149 [N/m^2]
wing stress (3 g) during operation : 122 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.22 ["]
max. angle of attack (stalling angle) : 12.70 ["]
angle of attack at max. speed : 8.21 ["]
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 : 0.78 [ ]
induced drag coefficient at max. speed : 0.0497 [ ]
drag coefficient at max. speed : 0.0834 [ ]
drag coefficient (zero lift) : 0.0338 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 53 [km/u]
stalling speed at sea-level (MTOW): 53 [km/u]
landing speed at sea-level: 62 [km/hr]
min. drag speed (max endurance) at cruise height : 59 [km/hr] (power:96 [%])
min. power speed (max range) : 73 [km/hr] at 250 [m] (power:116 [%])
max. rate of climb speed : 56.0 [km/hr] at sea-level
cruising speed : 58 [km/hr] op 250 [m] (power:96 [%])
design speed prop : 61 [km/hr]
maximum speed : 64 [km/hr] op 50 [m] (power:99 [%])
climbing speed at sea-level : 6 [m/min]
The Army Aeroplane with 60hp ENV F engine
calculation : *9* (regarding various performances)
take-off speed : 56.0 [km/u]
static prop wash : 58 [km/u]
take-off distance at sea-level : 191 [m]
lift/drag ratio : 9.46 [ ]
time to 100m : 19.29 [min]
practical ceiling (operational weight) : 93 [m] with flying weight :1118 [kg] line 3385
turning speed at CLmax : 53.4 [km/u] at 50 [m] height
turn radius at 50m: 95 [m]
time needed for 360* turn 40.4 [seconds] at 50m
load factor at max. angle turn 1.03 ["g"]
calculation *10* (action radius & endurance)
estimated endurance : 0.35 [hours] with 1 crew and possible useful load : 34.1 [kg] and 100.0 [%] fuel
published range : 20 [km] with 1 crew and 34.1 [kg] useful load and 100.0 [%] fuel
range : 114 [km] with 1 crew and 0.0 [kg] useful load and 568.1 [%] fuel
max range theoretically with additional fuel tanks for total 56.5 [litre] fuel : 113.6 [km]
useful load with range 500km : 0 [kg]
production (500 km) : 0 [tonkm/hour]
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Literature :
Historische vliegtuigen page 32,114
http://flyingmachines.ru/Site2/Crafts/Craft28343.htm
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 07 October 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4