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weight and performance calculations for the Nieuport 12A.2
1ste 12a's had a engine cowling that was open at the bottom, it looks like this is the case here. This could also well be the 12A.2 prototype.
Nieuport 12A.2
role : two-seat armed reconnaissance and artillery observation
importance : ****
first flight : operational : November 1915
country : France
design : Gustave Delage
production : unknown 300+
general information :
The Nieuport 10 with its 80 hp rotation engine was not powerful enough for a 2-person crew with equipment. To improve this, Delage designed the Nieuport 12 with the stronger 110 hp rotary engine. Later the 12C.2 (or 12bis) with 130 hp engine also appeared. It is not clear exactly how many numbers have been in use. The RFC identified them in their reports as Nieuport Scout without further specification. In addition to the movable machine gun for the observer, an extra machine gun was placed on the upper wing.
users : France, UK (RFC)
crew : 2
armament : 1 movable 7.70 [mm] (0.303 in) Lewis machine-gun for the observer
engine : 1 Clerget 9Z air-cooled 9 -cylinder two-valve rotary engine 110 [hp](80.9 KW)
dimensions :
wingspan : 9.03 [m], length : 7.0 [m], height : 2.67[m]
wing area : 22.0 [m^2]
weights :
max.take-off weight : 850 [kg]
empty weight operational : 550 [kg] bombload : 40 [kg]
performance :
maximum speed : 146 [km/u] op 2000 [m]
climbing speed : 197 [m/min]
service ceiling : 4000 [m]
endurance : 2.8 [hours]
estimated action radius : 181 [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 :0.63 [ ]
estimated diameter airscrew 2.73 [m]
angle of attack prop : 17.78 [ ]
reduction : 1.00 [ ]
airscrew revs : 1180 [r.p.m.]
pitch at Max speed 2.06 [m]
blade-tip speed at Vmax and max revs. : 173 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.22 [m]
calculated wing chord (rounded tips): 1.37 [m]
wing aspect ratio : 7.41 []
estimated gap : 1.41 [m]
gap/chord : 1.16 [ ]
seize (span*length*height) : 169 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 7.8 [kg/hr]
fuel consumption(cruise speed) : 26.7 [kg/hr] (36.4 [litre/hr]) at 70 [%] power
distance flown for 1 kg fuel : 4.93 [km/kg]
estimated total fuel capacity : 114 [litre] (83 [kg])
Nieuport 12 codé "2" de l'escadrille N 68 en 1916 - Remarquez l'insigne de l'escadrille mêlant le cor de chasse et le chiffre "68" - Photo collection David Méchin que je remercie pour son aide.
calculation : *3* (weight)
weight engine(s) dry : 166.0 [kg] = 2.05 [kg/KW]
weight 31 litre oil tank : 3.9 [kg]
oil tank filled with 0.6 litre oil : 0.5 [kg]
oil in engine 0 litre oil : 0.4 [kg]
fuel in engine 1 litre fuel : 0.4 [kg]
weight 15 litre gravity patrol tank(s) : 1.5 [kg]
weight cowling 3.2 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 191 [kg](22.5 [%])
***************************************************************
fuselage skeleton (wood gauge : 6.74 [cm]): 81 [kg]
bracing : 4.0 [kg]
fuselage covering ( 9.3 [m2] doped linen fabric) : 3.0 [kg]
weight controls + indicators: 5.6 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 2.8 [kg]
weight 98 [litre] main fuel tank empty : 9.4 [kg]
weight engine mounts & firewalls : 4 [kg]
total weight fuselage : 121 [kg](14.3 [%])
***************************************************************
weight wing covering (doped linen fabric) : 14 [kg]
total weight ribs (57 ribs) : 51 [kg]
load on front upper spar (clmax) per running metre : 1022.5 [N]
load on rear upper spar (vmax) per running metre : 279.4 [N]
total weight 6.0 spars : 48 [kg]
weight wings : 112 [kg]
weight wing/square meter : 5.11 [kg]
weight 4 interplane struts & cabane : 12.1 [kg]
weight cables (45 [m]) : 4.5 [kg] (= 100 [gram] per metre)
diameter cable : 4.0 [mm]
weight fin & rudder (0.9 [m2]) : 5.0 [kg]
weight stabilizer & elevator (2.5 [m2]): 12.8 [kg]
total weight wing surfaces & bracing : 147 [kg] (17.3 [%])
*******************************************************************
weight machine-gun(s) : 12.7 [kg]
weight pivot mounting mg :6.0 [kg]
weight armament : 19 [kg]
********************************************************************
wheel pressure : 425.0 [kg]
weight 2 wheels (690 [mm] by 81 [mm]) : 20.8 [kg]
weight tailskid : 2.7 [kg]
weight undercarriage with axle 24.3 [kg]
total weight landing gear : 47.8 [kg] (5.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 526 [kg](61.8 [%])
weight oil for 3.3 hours flying : 25.9 [kg]
weight 5 drums empty : 1.0 [kg]
weight ammunition (235 rounds) : 7.5 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 560 [kg] (65.9 [%])
published operational weight empty : 550 [kg] (64.7 [%])
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weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 53 [kg]
********************************************************************
operational weight : 776 [kg](91.2 [%])
bomb load : 40 [kg]
operational weight bombing mission : 816 [kg]
weight camera : 20 [kg]
operational weight photo mission : 796 [kg]
fuel reserve : 30 [kg] enough for 1.12 [hours] flying
possible additional useful load : 25 [kg]
operational weight fully loaded : 850 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 850 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 9.59 [kg/kW]
total power : 80.9 [kW] at 1180 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.9 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.7 [g]
design flight time : 2.20 [hours]
design cycles : 614 sorties, design hours : 1350 [hours]
operational wing loading : 355 [N/m^2]
wing stress (3 g) during operation : 208 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.19 ["]
max. angle of attack (stalling angle) : 12.47 ["]
angle of attack at max. speed : 3.78 ["]
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 : 0.42 [ ]
induced drag coefficient at max. speed : 0.0119 [ ]
drag coefficient at max. speed : 0.0536 [ ]
drag coefficient (zero lift) : 0.0417 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 80 [km/u]
landing speed at sea-level (OW without bombload): 96 [km/hr]
min. drag speed (max endurance) : 107 [km/hr] at 2000 [m](power :50 [%])
min. power speed (max range) : 119 [km/hr] at 2000 [m] (power:55 [%])
max. rate of climb speed : 96.5 [km/hr] at sea-level
cruising speed : 131 [km/hr] op 2000 [m] (power:64 [%])
design speed prop : 139 [km/hr]
maximum speed : 146 [km/hr] op 2000 [m] (power:78 [%])
climbing speed at sea-level (without bombload) : 193 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 248 [m]
lift/drag ratio : 9.38 [ ]
max. practical ceiling : 5325 [m] with flying weight :646 [kg]
practical ceiling (operational weight) : 4050 [m] with flying weight :776 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 3625 [m] with flying weight :823 [kg]
published ceiling (4000 [m]
climb to 1500m (without bombload) : 8.84 [min]
climb to 3000m (without bombload) : 22.83 [min]
max. dive speed : 372.0 [km/hr] at 2625 [m] height
load factor at max. angle turn 1.70 ["g"]
turn radius at 500m: 67 [m]
time needed for 360* turn 14.0 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 3.12 [hours] with 2 crew and 45 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 2.75 [hours] with 2 crew and possible useful (bomb) load : 55 [kg] and 88.1 [%] fuel
action radius : 266 [km] with 2 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 314 [litre] fuel : 1135 [km]
useful load with action-radius 250km : 129 [kg]
production : 16.92 [tonkm/hour]
oil and fuel consumption per tonkm : 2.04 [kg]
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Literature :
Praktisch handboek vliegtuigen deel 1 page 141
Fighters 1914-19 page 59
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
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(c) B van der Zalm 23 March 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4