Halberstadt CL.II
role : light ground attack aircraft and co-op
first flight : operational : August 1917
country : Germany
design :
production : 439 aircraft
general information :
First German aircraft of the CL-class. This class is for 2-seater with an empty weight below 730 kg. This class was dedicated to support the ground forces for which a smaller and more agile aircraft is more useful. They flew at the start of 1918 with all Slachtstaffeln and they harassed the allied ground forces.
Chord upper plane : 1.60m lower plane : 1.31m Gap, Maximum : 1.22m
Area of stabilo & elevator : 2.42 m2 area of rudder & fin : 1.33 m2
Capacity petrol tanks : 34 gallons = 155 litre oil : 4 gallons = 18.2 litre
Climb to 3048m : 24 min 30 sec rate of climb : 134 m/min
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.III liquid-cooled 6 -cylinder inline engine 163 [hp](119.9 KW)
dimensions :
wingspan : 10.77 [m], length : 7.32 [m], height : 2.75[m]
wing area : 27.5 [m^2]
weights :
max.take-off weight : 1133 [kg]
empty weight operational : 773 [kg] bombload : 0 [kg]
performance :
maximum speed : 156 [km/u] op 3000 [m]
service ceiling : 5100 [m]
endurance : 3.57 [hours]
estimated action radius : 251 [km]
description :
1-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 :0.64 [ ]
estimated diameter airscrew 2.86 [m]
angle of attack prop : 15.41 [ ]
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 1.86 [m]
blade-tip speed at Vmax and max revs. : 214 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.28 [m]
calculated wing chord (rounded tips): 1.41 [m]
wing aspect ratio : 8.44 []
estimated gap : 1.24 [m]
gap/chord : 0.97 [ ]
seize (span*length*height) : 217 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.5 [kg/hr]
fuel consumption(cruise speed) : 28.0 [kg/hr] (38.3 [litre/hr]) at 61 [%] power
distance flown for 1 kg fuel : 5.01 [km/kg]
estimated total fuel capacity : 155 [litre] (114 [kg])
calculation : *3* (weight)
weight engine(s) dry : 299.0 [kg] = 2.49 [kg/KW]
Pigeon messengers
weight 15 litre oil tank : 1.3 [kg]
oil tank filled with 0.9 litre oil : 0.8 [kg]
oil in engine 7 litre oil : 6.0 [kg]
fuel in engine 1 litre fuel : 0.6 [kg]
weight 16 litre gravity patrol tank(s) : 2.4 [kg]
weight radiator : 17.2 [kg]
weight exhaust pipes & fuel lines 11.1 [kg]
weight cowling 4.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 361 [kg](31.9 [%])
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fuselage skeleton (wood gauge : 6.40 [cm]): 77 [kg]
bracing : 4.0 [kg]
fuselage covering ( 10.1 [m2] doped linen fabric) : 3.2 [kg]
weight controls + indicators: 5.9 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 139 [litre] main fuel tank empty : 11.1 [kg]
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 118 [kg](10.4 [%])
***************************************************************
weight wing covering (doped linen fabric) : 18 [kg]
total weight ribs (73 ribs) : 67 [kg]
load on front upper spar (clmax) per running metre : 763.6 [N]
load on rear upper spar (vmax) per running metre : 307.9 [N]
total weight 8 spars : 51 [kg]
weight wings : 136 [kg]
weight wing/square meter : 4.93 [kg]
weight 4 interplane struts & cabane : 6.7 [kg]
weight cables (50 [m]) : 4.0 [kg] (= 80 [gram] per metre)
diameter cable : 3.6 [mm]
weight fin & rudder (1.3 [m2]) : 6.8 [kg]
weight stabilizer & elevator (3.1 [m2]): 15.5 [kg]
total weight wing surfaces & bracing : 169 [kg] (14.9 [%])
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weight machine-gun(s) : 26.5 [kg]
weight pivot mounting mg :6.9 [kg]
weight ammunition magazine(s) :2.3 [kg]
weight Fokker Zentralsteuerung synchronization gear : 1.0 [kg]
weight armament : 37 [kg]
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wheel pressure : 566.5 [kg]
weight 2 wheels (770 [mm] by 97 [mm]) : 20.2 [kg]
weight tailskid : 2.4 [kg]
weight undercarriage with axle 31.9 [kg]
total weight landing gear : 54.5 [kg] (4.8 [%]
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calculated empty weight : 739 [kg](65.2 [%])
weight oil for 4.3 hours flying : 10.8 [kg]
weight cooling fluids : 25.9 [kg]
weight 1 drums empty : 2.3 [kg]
weight ammunition (1000 rounds) : 30.5 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
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calculated operational weight empty : 811 [kg] (71.6 [%])
published operational weight empty : 773 [kg] (68.2 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 56 [kg]
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operational weight : 1029 [kg](90.8 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 1079 [kg]
fuel reserve : 54 [kg] enough for 1.92 [hours] flying
operational weight fully loaded : 1133 [kg] with fuel tank filled for 97 [%]
published maximum take-off weight : 1133 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 8.58 [kg/kW]
total power : 119.9 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.1 [g] at 1000 [m]
limit load : 3.25 [g] ultimate load : 4.9 [g] load factor : 1.9 [g]
design flight time : 2.86 [hours]
design cycles : 329 sorties, design hours : 940 [hours]
operational wing loading : 367 [N/m^2]
wing stress (3 g) during operation : 223 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.15 ["]
max. angle of attack (stalling angle) : 12.05 ["]
angle of attack at max. speed : 3.81 ["]
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 : 0.43 [ ]
induced drag coefficient at max. speed : 0.0124 [ ]
A CL.II being loaded with hand grenades. To the side of the fuselage is a rack for stick grenades. On the rear decking you can see the signal gun cartridges
drag coefficient at max. speed : 0.0508 [ ]
drag coefficient (zero lift) : 0.0384 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 82 [km/u]
landing speed at sea-level (OW without bombload): 99 [km/hr]
min. drag speed (max endurance) : 118 [km/hr] at 3000 [m](power :46 [%])
min. power speed (max range) : 130 [km/hr] at 3000 [m] (power:50 [%])
max. rate of climb speed : 103.5 [km/hr] at sea-level
cruising speed : 140 [km/hr] op 3000 [m] (power:56 [%])
design speed prop : 148 [km/hr]
maximum speed : 156 [km/hr] op 3000 [m] (power:68 [%])
climbing speed at sea-level (without bombload) : 237 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 189 [m]
lift/drag ratio : 9.85 [ ]
max. practical ceiling : 5775 [m] with flying weight :871 [kg]
practical ceiling (operational weight): 4675 [m] with flying weight :1029 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 4200 [m] with flying weight :1105 [kg]
published ceiling (5100 [m]
climb to 1500m (without bombload) : 7.10 [min]
climb to 3000m (without bombload) : 17.68 [min]
max. dive speed : 398.1 [km/hr] at 3200 [m] height
load factor at max. angle turn 1.90 ["g"]
turn radius at 500m: 66 [m]
time needed for 360* turn 12.8 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 3.92 [hours] with 2 crew and 50 [kg] useful (bomb)load and 96.9 [%] fuel
published endurance : 3.57 [hours] with 2 crew and possible useful (bomb) load : 60 [kg] and 88.1 [%] fuel
action radius : 351 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 377 [litre] fuel : 1384 [km]
useful load with action-radius 250km : 176 [kg]
production : 24.78 [tonkm/hour]
oil and fuel consumption per tonkm : 1.23 [kg]
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Literature :
Warplanes WW1 page 103,106f,119f
Fighters 1914-19 page 26,104
Praktisch handboek vliegtuigen deel 1 page 278
Jane’s fighting aircraft WWI page 160,162t
Note the teardrop fearing for the radio generator
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 23 September 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4