C.V/16 with radiators besides the fuselage
Albatros C.V
first flight : operational : June 1916
country : Germany
design : Thelen and Schubert
production : 424 aircraft
general information : New design after the successful C. III reconnaissance plane and
the departure off the designer Ernst Heinkel to Hansa-Brandenburg. It had a
more streamlined fuselage in which the engine was built in almost completely. Between the engine and the propeller was a reduction gear. It was well armed with a forward firing synchronized Spandau machine gun and a movable Parabellum machine gun for the observer. However, the C. V/16 was not easy to fly and had problems with engine cooling. This led to the improved C. V/17 with adapted lower wing and a displacement of the radiator to the upper wing. Also, it was struggling with crankshaft failures, so there were few active on the front between the spring of 1916 and early 1917. When the production of the Mercedes D. IV engine was stopped, the production of the C.V. was also abandoned. Albatros C.V carried out the first night bombing raid on London, when Offizierstellvertreter Klimke and his observer chose to attack the capital on the night of 6/7 May 1917. They dropped five 12.5kg bombs between Hackney and Holloway. They were reprimanded for their efforts, which came just before the first official raid was planned, but they were them moved to a bomber unit and took part in the night bombing campaign.
users : Germany
crew : 2
armament : 1 synchronized 7.92 [mm] (0.312 in) Spandau LMG 08/15 machine-gun
and 1 movable 7.92 [mm] (0.312 in) Parabellum MG 14 machine-gun for the observer
engine : 1 Mercedes D.IV liquid-cooled 8 -cylinder inline engine 220 [hp](161.8 KW)
dimensions :
wingspan : 12.75 [m], length : 8.94 [m], height : 3.55[m]
wing area : 43.4 [m^2]
weights :
max.take-off weight : 1585 [kg]
empty weight operational : 1069 [kg] bombload : 180 [kg]
Albatros C.V/17
performance :
maximum speed : 170 [km/hr] at sea-level
climbing speed : 126 [m/min]
service ceiling : 5180 [m]
estimated endurance : 4.0 [hours]
estimated action radius : 306 [km]
description :
2-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
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.63 [ ]
estimated diameter airscrew 3.11 [m]
angle of attack prop : 20.22 [ ]
Side view of the C. V/16 with radiators along side of the fuselage, this did not work well and was replaced in the C. V/17 with 1 radiator in the upper wing
reduction : 0.75 [ ]
airscrew revs : 1050 [r.p.m.]
pitch at Max speed 2.70 [m]
blade-tip speed at Vmax and max revs. : 177 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.70 [m]
calculated wing chord (rounded tips): 1.88 [m]
wing aspect ratio : 7.49 []
estimated gap : 1.73 [m]
gap/chord : 1.02 [ ]
seize (span*length*height) : 405 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.6 [kg/hr]
fuel consumption(cruise speed) : 40.6 [kg/hr] (55.4 [litre/hr]) at 66 [%] power
distance flown for 1 kg fuel : 3.77 [km/kg]
estimated total fuel capacity : 252 [litre] (184 [kg])
calculation : *3* (weight)
weight engine(s) dry : 365.0 [kg] = 2.26 [kg/KW]
weight reduction gear : 9.7 [kg]
weight 23 litre oil tank : 2.0 [kg]
oil tank filled with 1.2 litre oil : 1.1 [kg]
oil in engine 9 litre oil : 8.1 [kg]
fuel in engine 1 litre fuel : 0.8 [kg]
weight 24 litre gravity patrol tank(s) : 3.5 [kg]
weight radiator : 24.3 [kg]
weight exhaust pipes & fuel lines 15.2 [kg]
Top view of a C.V/17
weight self-starter : 4.0 [kg]
weight cowling 6.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 24.3 [kg]
total weight propulsion system : 472 [kg](29.8 [%])
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fuselage skeleton (wood gauge : 7.38 [cm]): 125 [kg]
bracing : 7.9 [kg]
fuselage covering ( 15.1 [m2] doped linen fabric) : 4.8 [kg]
weight controls + indicators: 6.6 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 12.6 [kg]
weight bomb sight : 1.0 [kg]
weight 228 [litre] main fuel tank empty : 18.2 [kg]
weight oxygen/compressed air flasks for high altitude : 8.7 [kg]
weight engine mounts & firewalls : 8 [kg]
total weight fuselage : 204 [kg](12.9 [%])
***************************************************************
weight wing covering (doped linen fabric) : 28 [kg]
total weight ribs (76 ribs) : 94 [kg]
load on front upper spar (clmax) per running metre : 811.6 [N]
load on rear upper spar (vmax) per running metre : 344.4 [N]
total weight 8 spars : 76 [kg]
weight wings : 198 [kg]
weight wing/square meter : 4.55 [kg]
weight 8 interplane struts & cabane : 26.1 [kg]
weight cables (75 [m]) : 9.0 [kg] (= 119 [gram] per metre)
diameter cable : 4.4 [mm]
weight fin & rudder (1.9 [m2]) : 8.9 [kg]
weight stabilizer & elevator (4.9 [m2]): 22.6 [kg]
total weight wing surfaces & bracing : 264 [kg] (16.7 [%])
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weight machine-gun(s) : 26.5 [kg]
weight pivot mounting mg :5.0 [kg]
weight ammunition magazine(s) :2.3 [kg]
weight synchronizing system : 1.0 [kg]
weight armament : 35 [kg]
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wheel pressure : 792.5 [kg]
weight 2 wheels (790 [mm] by 100 [mm]) : 32.8 [kg]
weight tailskid : 3.2 [kg]
weight undercarriage with axle 32.2 [kg]
total weight landing gear : 68.2 [kg] (4.3 [%]
*******************************************************************
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calculated empty weight : 1043 [kg](65.8 [%])
weight oil for 4.8 hours flying : 17.1 [kg]
weight cooling fluids : 35.0 [kg]
weight 1 drums empty : 2.3 [kg]
weight ammunition (1000 rounds) : 37.2 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 1133 [kg] (71.5 [%])
published operational weight empty : 1069 [kg] (67.4 [%])
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weight crew : 162 [kg]
weight (electrical heated) clothing for high altitude : 12.0 [kg]
weight fuel for 2.0 hours flying : 81 [kg]
********************************************************************
operational weight : 1389 [kg](87.6 [%])
bomb load : 180 [kg]
operational weight bombing mission : 1569 [kg]
fuel reserve : 16 [kg] enough for 0.40 [hours] flying
operational weight fully loaded : 1585 [kg] with fuel tank filled for 53 [%]
published maximum take-off weight : 1585 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 8.58 [kg/kW]
total power : 161.8 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.9 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 1.8 [g]
design flight time : 3.20 [hours]
design cycles : 211 sorties, design hours : 675 [hours]
operational wing loading : 314 [N/m^2]
wing stress (3 g) during operation : 207 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.19 ["]
max. angle of attack (stalling angle) : 12.44 ["]
angle of attack at max. speed : 1.57 ["]
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 : 0.23 [ ]
induced drag coefficient at max. speed : 0.0041 [ ]
drag coefficient at max. speed : 0.0364 [ ]
drag coefficient (zero lift) : 0.0323 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 76 [km/u]
landing speed at sea-level (OW without bombload): 91 [km/hr]
min. drag speed (max endurance) : 115 [km/hr] at 2590 [m](power :46 [%])
min. power speed (max range) : 123 [km/hr] at 2590 [m] (power:48 [%])
max. rate of climb speed : 105.3 [km/hr] at sea-level
cruising speed : 153 [km/hr] op 2590 [m] (power:66 [%])
design speed prop : 162 [km/hr]
maximum speed : 170 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 222 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 221 [m]
lift/drag ratio : 10.12 [ ]
max. practical ceiling : 5900 [m] with flying weight :1196 [kg]
practical ceiling (operational weight): 4850 [m] with flying weight :1389 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 4050 [m] with flying weight :1544 [kg]
published ceiling (5180 [m]
climb to 1500m (without bombload) : 7.53 [min]
climb to 3000m (without bombload) : 18.49 [min]
max. dive speed : 429.0 [km/hr] at 3050 [m] height
load factor at max. angle turn 1.85 ["g"]
turn radius at 500m: 57 [m]
time needed for 360* turn 12.1 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.70 [hours] with 2 crew and 180 [kg] bombload and 59.4 [%] fuel
published endurance : 4.00 [hours] with 2 crew and possible useful (bomb) load : 127 [kg] and 88.1 [%] fuel
action radius : 508 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 571 [litre] fuel : 1576 [km]
useful load with action-radius 250km : 286 [kg]
production : 43.72 [tonkm/hour]
oil and fuel consumption per tonkm : 1.01 [kg]
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Literature :
Flight magazine 28 feb 1918 > illustrations
Praktisch handboek vliegtuigen deel 1 page 264
Bombers 1914-19 page 121/122
Warplanes WOI page 18,61
Wikipedia
They fought for the sky page 93,94
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/content please mail to below mail
address
(c) B van der Zalm 21 August 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4
(c) B van der Zalm 19 may 2016 python 3.4.1
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