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Nieuport 28C.1
role : fighter
first flight : 14 juni 1917 operational : march 1918
country : France
design : Gustave Delage
production : 300 aircraft
general information : In the Nieuport 28 the single-spar lower wing and V-struts from its
predecessors were discarded and replaced by a two-spar wing with II-struts and
rounded tips.
In practise it proved under-powered and had a weak structure and it was not selected
by the French air force who already used the excellent SPAD-fighter.
The Americans however were in short supply of good fighters for the AEF and they
ordered 297 aircraft entering service march 1918.
chord upperwing : 1.3m lower wing : 1.0m
diameter airscrew : 2.5m
users : USAF (AEF 27th, 94th, 95th and 147th squadrons)
crew : 1
armament : 2 Vickers M6 7.7 [mm] (0.303 in) machine-guns
engine : 1 Gnome 9N Monosoupape air-cooled 9 -cylinder Monosoupape rotary engine
160 [hp](117.7 KW)
dimensions :
wingspan : 8.15 [m], length : 6.4 [m], height : 2.6[m]
wing area : 16.0 [m^2]
weights :
max.take-off weight : 737 [kg]
empty weight operational : 475 [kg] bombload : 0 [kg]
performance :
maximum speed : 196 [km/hr] at sea-level
climbing speed : 261 [m/min]
service ceiling : 5182 [m]
endurance : 1.5 [hours]
estimated action radius : 132 [km]
description :
1-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.64 [ ]
diameter airscrew 2.50 [m]
angle of attack prop : 22.33 [ ]
reduction : 1.00 [ ]
airscrew revs : 1350 [r.p.m.]
pitch at Max speed 2.42 [m]
blade-tip speed at Vmax and max revs. : 185 [m/s]
Nieuport 28 flown by Eddie Rickenbacker
calculation : *1* (dimensions)
mean wing chord : 0.98 [m]
calculated wing chord (rounded tips): 1.10 [m]
wing aspect ratio : 8.30 []
estimated gap : 1.12 [m]
gap/chord : 1.14 [ ]
seize (span*length*height) : 136 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 10.2 [kg/hr]
fuel consumption(cruise speed) : 30.1 [kg/hr] (41.1 [litre/hr]) at 76 [%] power
distance flown for 1 kg fuel : 5.86 [km/kg]
estimated total fuel capacity : 70 [litre] (51 [kg])
calculation : *3* (weight)
weight engine(s) dry : 154.0 [kg] = 1.31 [kg/KW]
weight 23 litre oil tank : 2.0 [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 17 litre gravity patrol tank(s) : 2.6 [kg]
weight cowling 4.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 182 [kg](24.7 [%])
***************************************************************
fuselage skeleton (wood gauge : 5.92 [cm]): 57 [kg]
bracing : 2.6 [kg]
fuselage covering ( 7.7 [m2] doped linen fabric) : 2.5 [kg]
weight controls + indicators: 5.3 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 52 [litre] main fuel tank empty : 4.2 [kg]
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 86 [kg](11.7 [%])
***************************************************************
weight wing covering (doped linen fabric) : 10 [kg]
total weight ribs (61 ribs) : 44 [kg]
load on front upper spar (clmax) per running metre : 890.2 [N]
load on rear upper spar (vmax) per running metre : 272.9 [N]
total weight 8 spars : 34 [kg]
weight wings : 88 [kg]
weight wing/square meter : 5.50 [kg]
weight 4 interplane struts & cabane : 4.7 [kg]
weight cables (39 [m]) : 2.1 [kg] (= 53 [gram] per metre)
diameter cable : 3.0 [mm]
weight fin & rudder (0.8 [m2]) : 4.4 [kg]
weight stabilizer & elevator (1.8 [m2]): 10.0 [kg]
total weight wing surfaces & bracing : 109 [kg] (14.8 [%])
*******************************************************************
weight machine-gun(s) : 31.8 [kg]
weight ammunition magazine(s) :2.7 [kg]
weight synchronizing system : 2.0 [kg]
weight armament : 37 [kg]
********************************************************************
wheel pressure : 368.5 [kg]
weight 2 wheels (740 [mm] by 87 [mm]) : 17.7 [kg]
weight tailskid : 2.1 [kg]
weight undercarriage with axle 18.7 [kg]
total weight landing gear : 38.5 [kg] (5.2 [%]
*******************************************************************
********************************************************************
calculated empty weight : 452 [kg](61.4 [%])
weight oil for 1.8 hours flying : 18.4 [kg]
weight ammunition (800 rounds) : 27.2 [kg]
weight signal pistol with cartridges : 3.6 [kg]
*******************************************************************
calculated operational weight empty : 502 [kg] (68.1 [%])
published operational weight empty : 475 [kg] (64.5 [%])
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weight crew : 81 [kg]
weight fuel for 1.5 hours flying : 45 [kg]
********************************************************************
operational weight : 628 [kg](85.2 [%])
estimated bomb load : 25 [kg]
operational weight bombing mission : 653 [kg]
fuel reserve : 6 [kg] enough for 0.20 [hours] flying
possible additional useful load : 78 [kg]
operational weight fully loaded : 737 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 737 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 5.33 [kg/kW]
total power : 117.7 [kW] at 1350 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.1 [g] at 1000 [m]
limit load : 4.5 [g] ultimate load : 6.8 [g] loadfactor : 2.4 [g]
design flight time : 1.20 [hours]
design cycles : 458 sorties, design hours : 550 [hours]
operational wing loading : 385 [N/m^2]
wing stress (3 g) during operation : 210 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.16 ["]
max.angle of attack (stalling angle) : 12.11 ["]
angle of attack at max.speed : 1.32 ["]
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 : 0.21 [ ]
induced drag coefficient at max.speed : 0.0031 [ ]
drag coefficient at max.speed : 0.0480 [ ]
drag coefficient (zero lift) : 0.0449 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 84 [km/u]
landing speed at sea-level (OW without bombload): 101 [km/hr]
min.drag speed (max endurance) : 114 [km/hr] at 2591 [m](power :34 [%])
min. power speed (max range) : 128 [km/hr] at 2591 [m] (power:37 [%])
max.rate of climb speed : 115.8 [km/hr] at sea-level
cruising speed : 176 [km/hr] op 2591 [m] (power:63 [%])
design speed prop : 190 [km/hr]
maximum speed : 196 [km/hr] op 100 [m] (power:100 [%])
climbing speed at sea-level (without bombload) : 399 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 220 [m]
lift/drag ratio : 9.04 [ ]
max. practical ceiling : 6825 [m] with flying weight :567 [kg]
practical ceiling (operational weight): 6375 [m] with flying weight :628 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 5800 [m] with flying weight :707 [kg]
published ceiling (5300 [m])
climb to 1500m (without bombload) : 3.73 [min]
climb to 3000m (without bombload) : 7.89 [min]
max.dive speed : 431.8 [km/hr] at 4800 [m] height
load factor at max.angle turn 2.53 ["g"]
turn radius at 500m: 64 [m]
time needed for 360* turn 10.5 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 1.70 [hours] with 1 crew and 103 [kg] useful (bomb)load
published endurance : 1.50 [hours] with 1 crew and possible useful (bomb) load : 109
[kg]
action radius : 394 [km] with 1 crew and 20[kg] bombload
max range theoretically with additional fuel tanks for total 253 [litre] fuel : 1085 [km]
useful load with action-radius 250km : 100 [kg]
production : 17.61 [tonkm/hour]
oil and fuel consumption per tonkm : 2.29 [kg]
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Notes : published ceiling 5300m seems to low
notes 
1st Lieutenant Edward V. Rickenbacker in the cockpit of a Nieuport 28 C.1
literatuur : wikepedia
Jane's Fighting aircraft WWI
Munson - fighters 1914-19 page 63
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
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(c) B van der Zalm 30 november 2018 contact : bvanderzalm@ziggo.nl python 3.4.1