Siemens-Schuckert D.III
fighter aircraft Siemens-Schuckert D.III *** April 1918
role : fighter
first flight : operational : April 1918
country : Germany
design :
production : 80 aircraft
general information : High rate of climb.
The contra-rotating rotary engine crankshaft rotated in opposite direction to the
cylinders. Advantage > less gyroscopic forces, lower rpm > 1800 rpm reduced to 900 rpm
> gave lower acceleration forces on the engine parts.
Disadvantage > reduced cooling of the cylinders > tendency to overheat. The D.III’s were returned to the factory to adjust the cooling problem. Then also the high-compression SH.IIIa engine was installed. Returning to service July 1918 The D.III did well as home defence fighter.
users : Luftwaffe
crew : 1
armament : 2 synchronized 7.92 [mm] (0.312 in) Spandau LMG 08/15 machine-guns
engine : 1 Siemens-Halske SH.IIIa air-cooled 11 -cylinder two-valve bi-rotary engine 160 [hp](117.7 KW)
dimensions :
wingspan : 8.43 [m], length : 5.7 [m], height : 2.8[m]
wing area : 18.9 [m^2]
weights :
max.take-off weight : 725 [kg]
empty weight operational : 534 [kg] bombload : 0 [kg]
performance :
maximum speed : 180 [km/hr] at sea-level
service ceiling : 8077 [m]
endurance : 2.0 [hours]
estimated action radius : 162 [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 4 -bladed tractor airscrew with max. efficiency :0.58 [ ]
estimated diameter airscrew 2.86 [m]
angle of attack prop : 30.36 [ ]
coarse pitch
reduction : 0.50 [ ]
airscrew revs : 760 [r.p.m.]
pitch at Max speed 3.95 [m]
blade-tip speed at Vmax and max revs. : 124 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.12 [m]
calculated wing chord (rounded tips): 1.26 [m]
wing aspect ratio : 7.52 []
estimated gap : 1.25 [m]
gap/chord : 1.12 [ ]
seize (span*length*height) : 135 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 4.1 [kg/hr]
fuel consumption(cruise speed) : 38.2 [kg/hr] (52.1 [litre/hr]) at 86 [%] power
distance flown for 1 kg fuel : 4.25 [km/kg]
estimated total fuel capacity : 118 [litre] (87 [kg])
calculation : *3* (weight)
weight engine(s) dry : 198.0 [kg] = 1.68 [kg/KW]
weight reduction gear : 1.2 [kg]
weight 14 litre oil tank : 1.2 [kg]
oil tank filled with 0.9 litre oil : 0.8 [kg]
oil in engine 1 litre oil : 0.6 [kg]
fuel in engine 1 litre fuel : 0.6 [kg]
weight 22 litre gravity patrol tank(s) : 3.3 [kg]
weight cowling 4.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 41.2 [kg]
total weight propulsion system : 252 [kg](34.7 [%])
***************************************************************
fuselage skeleton (wood gauge : 5.23 [cm]): 40 [kg]
bracing : 1.6 [kg]
fuselage covering ( 6.1 [m2] doped linen fabric) : 2.0 [kg]
weight controls + indicators: 5.2 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 96 [litre] main fuel tank empty : 7.7 [kg]
weight oxygen/compressed air flasks for high altitude : 2.2 [kg]
D.III of Ernst Udet
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 73 [kg](10.0 [%])
***************************************************************
weight wing covering (doped linen fabric) : 12 [kg]
total weight ribs (53 ribs) : 43 [kg]
load on front upper spar (clmax) per running metre : 658.2 [N]
load on rear upper spar (vmax) per running metre : 254.2 [N]
total weight 8 spars : 27 [kg]
weight wings : 82 [kg]
weight wing/square meter : 4.34 [kg]
weight 4 interplane struts & cabane : 5.7 [kg]
weight cables (41 [m]) : 1.7 [kg] (= 42 [gram] per metre)
diameter cable : 2.6 [mm]
weight fin & rudder (0.8 [m2]) : 3.7 [kg]
weight stabilizer & elevator (2.1 [m2]): 9.4 [kg]
total weight wing surfaces & bracing : 102 [kg] (14.1 [%])
*******************************************************************
weight machine-gun(s) : 34.0 [kg]
weight ammunition magazine(s) :3.5 [kg]
weight synchronizing system : 2.0 [kg]
weight armament : 40 [kg]
********************************************************************
Ernst Udet in his D.III
wheel pressure : 362.5 [kg]
weight 2 wheels (720 [mm] by 86 [mm]) : 16.1 [kg]
weight tailskid : 1.6 [kg]
weight undercarriage with axle 14.9 [kg]
total weight landing gear : 32.6 [kg] (4.5 [%]
*******************************************************************
********************************************************************
calculated empty weight : 499 [kg](68.8 [%])
weight oil for 2.4 hours flying : 9.9 [kg]
weight ammunition (1000 rounds) : 35.0 [kg]
weight signal pistol with cartridges : 3.6 [kg]
*******************************************************************
calculated operational weight empty : 547 [kg] (75.5 [%])
published operational weight empty : 534 [kg] (73.7 [%])
_____________
| o |
-------------
"
weight crew : 81 [kg]
weight (electrical heated) clothing for high altitude : 6.0 [kg]
weight fuel for 1.5 hours flying : 57 [kg]
********************************************************************
operational weight : 691 [kg](95.4 [%])
estimated bomb load : 25 [kg]
operational weight bombing mission : 716 [kg]
fuel reserve : 9 [kg] enough for 0.23 [hours] flying
operational weight fully loaded : 725 [kg] with fuel tank filled for 76 [%]
published maximum take-off weight : 725 [kg] (100.0 [%])
||
I||==|
||
calculation : * 4 * (engine power)
power loading (operational without bombload) : 5.87 [kg/kW]
total power : 117.7 [kW] at 1520 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.8 [g] at 1000 [m]
limit load : 4.5 [g] ultimate load : 6.8 [g] loadfactor : 1.9 [g]
design flight time : 1.60 [hours]
design cycles : 250 sorties, design hours : 400 [hours]
operational wing loading : 359 [N/m^2]
wing stress (3 g) during operation : 248 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -2.02 ["]
max.angle of attack (stalling angle) : 11.60 ["]
angle of attack at max.speed : 0.79 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.17 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max.speed : 0.24 [ ]
induced drag coefficient at max.speed : 0.0042 [ ]
drag coefficient at max.speed : 0.0472 [ ]
drag coefficient (zero lift) : 0.0430 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 81 [km/u]
landing speed at sea-level (OW without bombload): 98 [km/hr]
min.drag speed (max endurance) : 123 [km/hr] at 4038 [m](power :43 [%])
min. power speed (max range) : 136 [km/hr] at 4038 [m] (power:46 [%])
max.rate of climb speed : 109.1 [km/hr] at sea-level
cruising speed : 162 [km/hr] op 4038 [m] (power:60 [%])
design speed prop : 175 [km/hr]
maximum speed : 180 [km/hr] op 100 [m] (power:100 [%])
climbing speed at sea-level (without bombload) : 305 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 193 [m]
lift/drag ratio : 8.79 [ ]
max. practical ceiling : 8275 [m] with flying weight :609 [kg]
practical ceiling (operational weight): 7625 [m] with flying weight :691 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 7650 [m] with flying weight :687 [kg]
published ceiling (8077 [m]
climb to 1500m (without bombload) : 4.89 [min]
climb to 3000m (without bombload) : 9.71 [min]
max.dive speed : 420.4 [km/hr] at 6650 [m] height
load factor at max.angle turn 2.16 ["g"]
turn radius at 500m: 62 [m]
time needed for 360* turn 11.4 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.02 [hours] with 1 crew and 20 [kg] useful load and 88.8 [%] fuel
published endurance : 2.00 [hours] with 1 crew and possible useful (bomb) load : 21 [kg] and 88.1 [%] fuel
action radius : 163 [km] with 1 crew and 20[kg] photo camera/radio transmitter or
bombload
max range theoretically with additional fuel tanks for total 185 [litre] fuel : 575 [km]
useful load with action-radius 250km : 18 [kg]
production : 2.87 [tonkm/hour]
oil and fuel consumption per tonkm : 14.73 [kg]
_
I_°==/
°
Literature :
Warplanes WW1 page 133
Praktisch handboek vliegtuigen deel 1 page 282
Fighters 1914-19 page 72
last check python :
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 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.2(32-bit)