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weight and performance calculations for the Nieuport 23
© bvdz, Belgian Nieuport 23 on display in Royal military museum in Brussel 2019
Nieuport 23
role : fighter
importance : ***
first flight : operational : June 1917
country : France
design :
production : unknown
general information :
Mostly identical to the Nieuport 17. It had a more powerful engine and a different
synchronization gear for the Vickers machine gun. The gun was offset to starboard and
the fuel and oil tank arrangement and the centre section rigging were changed.
users : France, RFC (80) , Belgium
crew : 1
armament : 1 synchronized 7.70 [mm] (0.303 in) Vickers machine-gun
engine : 1 Le Rhone 9jb air-cooled 9 -cylinder two-valve rotary engine 120 [hp](88.3 KW)
dimensions :
wingspan : 8.15 [m], length : 5.97 [m], height : 2.44[m]
wing area : 15.0 [m^2]
weights :
max.take-off weight : 560 [kg]
empty weight operational : 375 [kg] bombload : 0 [kg]
performance :
maximum speed : 166 [km/hr] at sea-level
climbing speed : 261 [m/min]
service ceiling : 5300 [m]
endurance : 2.0 [hours]
estimated action radius : 149 [km]
description :
1-bay biplane with fixed landing gear and tail strut
upper wing 2 spars, lower wing single spar
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 2.42 [m]
angle of attack prop : 22.88 [ ]
reduction : 1.00 [ ]
airscrew revs : 1150 [r.p.m.]
pitch at Max speed 2.41 [m]
blade-tip speed at Vmax and max revs. : 153 [m/s]
calculation : *1* (dimensions)
mean wing chord : 0.92 [m]
calculated wing chord (rounded tips): 1.03 [m]
wing aspect ratio : 8.86 []
estimated gap : 1.10 [m]
gap/chord : 1.20 [ ]
seize (span*length*height) : 119 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 5.1 [kg/hr]
fuel consumption(cruise speed) : 23.9 [kg/hr] (32.6 [litre/hr]) at 60 [%] power
distance flown for 1 kg fuel : 6.26 [km/kg]
estimated total fuel capacity : 74 [litre] (54 [kg])
calculation : *3* (weight)
weight engine(s) dry : 140.0 [kg] = 1.59 [kg/KW]
weight 16 litre oil tank : 2.0 [kg]
oil tank filled with 0.7 litre oil : 0.6 [kg]
oil in engine 0 litre oil : 0.4 [kg]
fuel in engine 1 litre fuel : 0.4 [kg]
weight 14 litre gravity patrol tank(s) : 1.4 [kg]
weight cowling 3.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 165 [kg](29.5 [%])
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fuselage skeleton (wood gauge : 5.09 [cm]): 40 [kg]
Sous-Lieutenant Robert “Bob” De Leener as Flight Commander of N° 10 fighter squadron in his Nieuport 23.
bracing : 1.7 [kg]
fuselage covering ( 6.7 [m2] doped linen fabric) : 2.2 [kg]
weight controls + indicators: 5.2 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 60 [litre] main fuel tank empty : 5.8 [kg]
weight engine mounts & firewalls : 4 [kg]
total weight fuselage : 67 [kg](11.9 [%])
***************************************************************
weight wing covering (doped linen fabric) : 10 [kg]
total weight ribs (50 ribs) : 33 [kg]
load on front upper spar (clmax) per running metre : 660.2 [N]
load on rear upper spar (vmax) per running metre : 208.2 [N]
total weight 6.0 spars : 25 [kg]
weight wings : 68 [kg]
weight wing/square meter : 4.53 [kg]
weight 4 interplane struts & cabane : 4.4 [kg]
weight cables (39 [m]) : 2.1 [kg] (= 53 [gram] per metre)
diameter cable : 2.9 [mm]
Landing accident of Nieuport 23 flown by Max Orban , according to Walter M.Pieters in his superb book “ Over Flanders fields ” this could be N5024 now on display in the Royal Military Museum in Brussel
weight fin & rudder (0.8 [m2]) : 3.6 [kg]
weight stabilizer & elevator (1.7 [m2]): 7.8 [kg]
total weight wing surfaces & bracing : 86 [kg] (15.3 [%])
*******************************************************************
weight machine-gun(s) : 15.9 [kg]
weight ammunition magazine(s) :1.8 [kg]
weight Alkan-Hamy synchronization gear : 1.0 [kg]
weight armament : 19 [kg]
********************************************************************
wheel pressure : 280.0 [kg]
weight 2 wheels (690 [mm] by 81 [mm]) : 12.3 [kg]
weight tailskid : 1.5 [kg]
weight undercarriage with axle 14.0 [kg]
total weight landing gear : 27.8 [kg] (5.0 [%]
*******************************************************************
********************************************************************
calculated empty weight : 365 [kg](65.1 [%])
weight oil for 2.4 hours flying : 12.3 [kg]
weight ammunition (400 rounds) : 11.0 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 393 [kg] (70.1 [%])
published operational weight empty : 375 [kg] (67.0 [%])
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weight crew : 81 [kg]
weight fuel for 1.5 hours flying : 36 [kg]
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S/Lt Edmond Thieffry , Belgian WWI ace in front of his Nieuport 23
operational weight : 509 [kg](91.0 [%])
estimated bomb load : 25 [kg]
operational weight bombing mission : 534 [kg]
fuel reserve : 18 [kg] enough for 0.77 [hours] flying
possible additional useful load : 7 [kg]
operational weight fully loaded : 560 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 560 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 5.77 [kg/kW]
total power : 88.3 [kW] at 1150 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.6 [g] at 1000 [m]
limit load : 4.5 [g] ultimate load : 6.8 [g] load factor : 2.4 [g]
design flight time : 1.60 [hours]
Nieuport 23 of J.l.Semyonov, CO of the 9
th
army, southern front summer 1920
design cycles : 375 sorties, design hours : 600 [hours]
operational wing loading : 333 [N/m^2]
wing stress (3 g) during operation : 220 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.14 ["]
max. angle of attack (stalling angle) : 11.87 ["]
angle of attack at max. speed : 1.81 ["]
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 : 0.26 [ ]
induced drag coefficient at max. speed : 0.0038 [ ]
drag coefficient at max. speed : 0.0620 [ ]
drag coefficient (zero lift) : 0.0582 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 79 [km/u]
landing speed at sea-level (OW without bombload): 94 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 99 [km/hr] at 2650 [m] (power:33 [%])
min. power speed (max range) : 112 [km/hr] at 2650 [m] (power:37 [%])
max. rate of climb speed : 98.0 [km/hr] at sea-level
cruising speed : 149 [km/hr] op 2650 [m] (power:61 [%])
design speed prop : 161 [km/hr]
maximum speed : 166 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 373 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 176 [m]
lift/drag ratio : 8.68 [ ]
max. practical ceiling : 5700 [m] with flying weight :470 [kg]
practical ceiling (operational weight) : 5325 [m] with flying weight :509 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 5100 [m] with flying weight :536 [kg]
published ceiling (5300 [m]
climb to 1500m (without bombload) : 4.49 [min]
climb to 3000m (without bombload) : 10.99 [min]
max. dive speed : 356.6 [km/hr] at 4100 [m] height
load factor at max. angle turn 2.45 ["g"]
turn radius at 500m: 56 [m]
time needed for 360* turn 10.0 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.27 [hours] with 1 crew and 32 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 2.00 [hours] with 1 crew and possible useful (bomb) load : 39 [kg] and 88.1 [%] fuel
action radius : 208 [km] with 1 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 139 [litre] fuel : 639 [km]
useful load with action-radius 250km : 22 [kg]
production : 3.32 [tonkm/hour]
oil and fuel consumption per tonkm : 8.75 [kg]
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Literature :
Jane’s Fighting aircraft WWI page 119,120
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