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weight and performance calculations for the Rumpler 6B1
Rumpler 6B1
role : light maritime single-seat scout (ship based)
importance : ***
first flight : operational : July 1916
country : Germany
design :
production : 457 aircraft
general information :
Water-borne fighter designed for the German Navy to defend its seaplane bases and coastal areas. It was developed from Rumpler C.I reconnaissance airplane. The first 6B1 was delivered in July 1916 and by May 1917 38 aircraft had entered service. They operated at Zeebrugge and Ostend and some were employed in the Black Sea to counter Russian flying boats. In October 1917 the 6B2 entered service. This variant was based on the C.IV and had bigger dimensions. Despite poorer performance 50 aircraft were delivered.
users : Germany
crew : 1
armament : 1 synchronized 7.92 [mm] (0.312 in) Spandau machine-gun
engine : 1 Mercedes D.III liquid-cooled 6 -cylinder inline engine 163 [hp](119.9 KW)
dimensions :
wingspan : 12.05 [m], length : 9.4 [m], height : 3.6[m]
wing area : 36.0 [m^2]
weights :
max.take-off weight : 1140 [kg]
empty weight operational : 790 [kg] bombload : 0 [kg]
performance :
maximum speed : 153 [km/hr] at sea-level
service ceiling : 5000 [m]
endurance : 4.0 [hours]
estimated action radius : 275 [km]
description :
2-bay two float biplane no tip floats
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 3.04 [m]
angle of attack prop : 14.27 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 1.82 [m]
blade-tip speed at Vmax and max revs. : 227 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.49 [m]
calculated wing chord (rounded tips): 1.65 [m]
wing aspect ratio : 8.07 []
estimated gap : 1.52 [m]
gap/chord : 1.02 [ ]
seize (span*length*height) : 408 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.5 [kg/hr]
fuel consumption(cruise speed) : 29.9 [kg/hr] (40.8 [litre/hr]) at 66 [%] power
distance flown for 1 kg fuel : 4.61 [km/kg]
estimated total fuel capacity : 185 [litre] (136 [kg])
calculation : *3* (weight)
weight engine(s) dry : 299.0 [kg] = 2.49 [kg/KW]
weight 16 litre oil tank : 2.1 [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 17 litre gravity patrol tank(s) : 1.7 [kg]
weight radiator : 17.2 [kg]
weight exhaust pipes & fuel lines 11.9 [kg]
weight cowling 4.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 361 [kg](31.7 [%])
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fuselage skeleton (wood gauge : 6.08 [cm]): 78 [kg]
bracing : 4.6 [kg]
fuselage covering ( 12.9 [m2] doped linen fabric) : 4.1 [kg]
weight controls + indicators: 6.3 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 168 [litre] main fuel tank empty : 16.1 [kg]
weight oxygen/compressed air flasks for high altitude : 4.3 [kg]
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 128 [kg](11.2 [%])
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weight wing covering (doped linen fabric) : 23 [kg]
total weight ribs (62 ribs) : 68 [kg]
load on front upper spar (clmax) per running metre : 654.6 [N]
load on rear upper spar (vmax) per running metre : 265.2 [N]
total weight 8 spars : 54 [kg]
weight wings : 145 [kg]
weight wing/square meter : 4.03 [kg]
weight 8 interplane struts & cabane : 15.5 [kg]
weight cables (69 [m]) : 5.9 [kg] (= 86 [gram] per metre)
diameter cable : 3.7 [mm]
weight fin & rudder (2.1 [m2]) : 8.8 [kg]
weight stabilizer & elevator (4.0 [m2]): 16.6 [kg]
total weight wing surfaces & bracing : 192 [kg] (16.9 [%])
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weight machine-gun(s) : 9.5 [kg]
weight ammunition magazine(s) :2.3 [kg]
weight Fokker Stangensteuerung synchronization gear : 1.0 [kg]
weight armament : 13 [kg]
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weight floats : 79 [kg] (6.9 [%])
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calculated empty weight : 772 [kg](67.8 [%])
weight oil for 4.8 hours flying : 12.1 [kg]
weight cooling fluids : 24.7 [kg]
weight ammunition (500 rounds) : 14.1 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
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calculated operational weight empty : 824 [kg] (72.3 [%])
published operational weight empty : 790 [kg] (69.3 [%])
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weight crew : 81 [kg]
weight (electrical heated) clothing for high altitude : 6.0 [kg]
On August 23, 1917, a 6B-2 was forced to land on the Zuiderzee, near Elburg, and was interned in the Netherlands. It was registered U1 and shipped to Tandjong Priok in Indonesia in July 1918. On May 22, 1919, it set a record for India by climbing to a height of 4625m. As a single-seater it was not usable for maritime patrol and ASW-duties (anti-submarine) and it was decided to convert it to a 2-seater. However, on the flight as a 2-seater, the plane skidded and ended up prematurely in the water, badly damaging it. After which it was probably written off.
weight fuel for 2.0 hours flying : 60 [kg]
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operational weight : 971 [kg](85.2 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 1021 [kg]
fuel reserve : 76 [kg] enough for 2.54 [hours] flying
possible additional useful load : 43 [kg]
operational weight fully loaded : 1140 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 1140 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 8.10 [kg/kW]
total power : 119.9 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.8 [g] at 1000 [m]
limit load : 3.5 [g] ultimate load : 5.2 [g] load factor : 1.9 [g]
design flight time : 3.20 [hours]
design cycles : 266 sorties, design hours : 850 [hours]
operational wing loading : 265 [N/m^2]
wing stress (3 g) during operation : 197 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.17 ["]
max. angle of attack (stalling angle) : 12.20 ["]
angle of attack at max. speed : 1.65 ["]
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 : 0.24 [ ]
induced drag coefficient at max. speed : 0.0041 [ ]
drag coefficient at max. speed : 0.0446 [ ]
drag coefficient (zero lift) : 0.0405 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 70 [km/u]
landing speed at sea-level (OW without bombload): 84 [km/hr]
min. drag speed (max endurance) : 97 [km/hr] at 2500 [m](power :41 [%])
min. power speed (max range) : 107 [km/hr] at 2500 [m] (power:44 [%])
max. rate of climb speed : 93.0 [km/hr] at sea-level
cruising speed : 138 [km/hr] op 2500 [m] (power:64 [%])
design speed prop : 145 [km/hr]
maximum speed : 153 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 248 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 124 [m]
lift/drag ratio : 9.39 [ ]
max. practical ceiling : 5625 [m] with flying weight :905 [kg]
practical ceiling (operational weight) : 5175 [m] with flying weight :971 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 4275 [m] with flying weight :1110 [kg]
published ceiling (5000 [m]
climb to 1500m (without bombload) : 6.71 [min]
climb to 3000m (without bombload) : 16.28 [min]
max. dive speed : 339.2 [km/hr] at 3275 [m] height
load factor at max. angle turn 2.07 ["g"]
turn radius at 500m: 46 [m]
time needed for 360* turn 10.1 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 4.54 [hours] with 1 crew and 99 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 4.00 [hours] with 1 crew and possible useful (bomb) load : 115 [kg] and 88.1 [%] fuel
action radius : 494 [km] with 1 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 341 [litre] fuel : 1152 [km]
useful load with action-radius 250km : 141 [kg]
production : 19.47 [tonkm/hour]
oil and fuel consumption per tonkm : 1.66 [kg]
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Literature :
Van Farman tot Neptune page 28,54
Praktisch handboek vliegtuigen deel 1 page 267
Fighters 1914-19 page 91,167
German aircraft of WWI page 527
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 March 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4