AIRCRAFT INVESTIGATION
weight and performance calculations for the Nieuport IIN
Nieuport IIN in the muse de l’air et l’espace in Paris, Le Bourget
Nieuport IIN
role : experimental/research/flying trials
importance : ****
first flight : operational : May 1911
country : France
design : Edouard Nieuport (1875-1911)
production : about 70
general information :
Edouard de Nieuport set three records for speed at Chalons, 11 May 1911 120 km/hr, 16 June 1911 130 km/hr and on 21 June 1911 133 km/hr. With a 50hp Gnome engine Jan Olieslagers set a record for distance in a closed circuit on 16 July 1911 at Kiewit (Belgium) with a distance of 625 km. Unfortunately Eduard Nieuport crashed with his airplane on 16 September 1911, he was fatally wounded.
With Nieuport engine it was indicated as IIN, with Gnome engine it was indicated as IIG.
On 28 December 1913 Georges Legagneux set the world height record at 6120m above St.Raphael, his Nieuport was fitted with a 80hp Le Rhone engine.
users : Edouard de Nieuport, Jan Olieslagers
crew : 1
engine : 1 Nieuport flat twin air-cooled horizontally opposed two-cylinder flat twin piston engine 28 [hp](20.9 KW)
dimensions :
wingspan : 8.65 [m], length : 7.2 [m], height : 2.6[m]
wing area : 14.0 [m^2]
weights :
max.take-off weight : 350 [kg]
empty weight operational : 240 [kg] useful load : 0 [kg]
performance :
maximum speed :120 [km/hr] at sea-level
cruise speed :108 [km/u] op 50 [m]
service ceiling : 650 [m]
endurance : 3.0 [hours]
range : 324 [km]
description :
low-wing monoplane with fixed landing gear and tail strut
two spar wing
engines, landing gear, fuel and useful load in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.61 [ ]
estimated diameter airscrew 2.30 [m]
angle of attack prop : 15.85 [ ]
reduction : 1.00 [ ]
airscrew revs : 1300 [r.p.m.]
pitch at Max speed 1.54 [m]
blade-tip speed at Vmax and max revs. : 160 [m/s]
calculation : *1* (dimensions)
wing chord : 1.89 [m]
mean wing chord : 1.62 [m]
calculated wing chord (rounded tips): 1.96 [m]
wing aspect ratio : 5.34 []
seize (span*length*height) : 162 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 0.8 [kg/hr]
fuel consumption(cruise speed) : 7.7 [kg/hr] (10.5 [litre/hr]) at 86 [%] power
distance flown for 1 kg fuel : 14.06 [km/kg] at 325 [m] cruise height, sfc : 427.9 [kg/kwh]
estimated total fuel capacity : 35.69 [litre] (26.16 [kg])
calculation : *3* (weight)
weight engine(s) dry : 75.2 [kg] = 3.60 [kg/KW]
weight 3.9 litre oil tank : 0.33 [kg]
oil tank filled with 0.2 litre oil : 0.1 [kg]
oil in engine 0.1 litre oil : 0.1 [kg]
fuel in engine 0.1 litre fuel : 0.10 [kg]
weight 4.5 litre gravity patrol tank(s) : 0.7 [kg]
weight cowling 0.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 6.2 [kg]
total weight propulsion system : 83 [kg](23.8 [%])
***************************************************************
fuselage skeleton (wood gauge : 4.67 [cm]): 40 [kg]
bracing : 2.0 [kg]
fuselage covering ( 9.8 [m2] doped linen fabric) : 3.1 [kg]
weight instruments. : 1.1 [kg]
weight controls : 4.1 [kg]
weight seats : 3.0 [kg]
weight 31 [litre] main fuel tank empty : 2.5 [kg]
weight engine mount : 1.0 [kg]
total weight fuselage : 57 [kg](16.3 [%])
***************************************************************
weight wing covering (doped linen fabric) : 19 [kg]
total weight ribs (18 ribs) : 21 [kg]
load on front upper spar (clmax) per running metre : 464.7 [N]
total weight 4 spars : 20 [kg]
weight wings : 60 [kg]
weight wing/square meter : 4.25 [kg]
weight cables (35 [m]) : 5.7 [kg] (= 166 [gram] per metre)
diameter cable : 5.2 [mm]
weight fin & rudder (0.9 [m2]) : 3.8 [kg]
weight stabilizer & elevator (1.6 [m2]): 6.8 [kg]
total weight wing surfaces & bracing : 76 [kg] (21.7 [%])
*******************************************************************
wheel pressure : 175.0 [kg]
weight 2 wheels (540 [mm] by 64 [mm]) : 10.6 [kg]
weight tailskid : 1.3 [kg]
weight undercarriage with axle 9.8 [kg]
total weight landing gear : 21.8 [kg] (6.2 [%]
*******************************************************************
Edouard Nieuport besides his IIN monoplane with flat twin engine
********************************************************************
calculated empty weight : 238 [kg](68.0 [%])
weight oil for 3.6 hours flying : 3.0 [kg]
calculated operational weight empty : 241 [kg] (68.8 [%])
published operational weight empty : 240 [kg] (68.6 [%])
___o___
"
weight crew : 81 [kg]
weight fuel for 1.0 hours flying : 8 [kg]
********************************************************************
operational weight : 330 [kg](94.2 [%])
fuel reserve : 18.5 [kg] enough for 2.40 [hours] flying
possible additional useful load : 2 [kg]
operational weight fully loaded : 350 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 350 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 16.76 [kg/kW]
power loading (operational without useful load) : 15.78 [kg/kW]
total power : 20.9 [kW] at 1300 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.8 [g] at 1000 [m]
limit load : 3.5 [g] ultimate load : 5.2 [g] load factor : 3.2 [g]
design flight time : 2.40 [hours]
design cycles : 306 sorties, design hours : 220 [hours]
operational wing loading : 231 [N/m^2]
wing stress (3 g) during operation : 163 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.31 ["]
max. angle of attack (stalling angle) : 13.28 ["]
angle of attack at max. speed : 3.17 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.11 [ ]
lift coefficient at max. speed : 0.34 [ ]
induced drag coefficient at max. speed : 0.0092 [ ]
drag coefficient at max. speed : 0.0401 [ ]
drag coefficient (zero lift) : 0.0309 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 66 [km/u]
stalling speed at sea-level (MTOW): 68 [km/u]
landing speed at sea-level: 78 [km/hr]
min. drag speed (max endurance) : 90 [km/hr] at 325 [m](power :65 [%])
min. power speed (max range) : 96 [km/hr] at 325 [m] (power:69 [%])
max. rate of climb speed : 82.0 [km/hr] at sea-level
cruising speed : 108 [km/hr] op 325 [m] (power:80 [%])
design speed prop : 114 [km/hr]
maximum speed : 120 [km/hr] op 50 [m] (power:99 [%])
climbing speed at sea-level : 82 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 75.2 [km/u]
static prop wash : 85 [km/u]
take-off distance at sea-level : 65 [m]
lift/drag ratio : 10.09 [ ]
max. theoretical ceiling : 2733 [m] with flying weight :324 [kg] line 3370
time to 1000m : 16.96 [min]
time to 1500m : 31.45 [min]
time to 2000m : 57.62 [min]
published ceiling (650 [m]
practical ceiling (operational weight) : 2493 [m] with flying weight :330 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 2168 [m] with flying weight :346 [kg]
max. dive speed : 286.5 [km/hr] at 1168 [m] height
turning speed at CLmax : 78.8 [km/u] at 50 [m] height
turn radius at 50m: 50 [m]
time needed for 360* turn 14.2 [seconds] at 50m
load factor at max. angle turn 1.41 ["g"]
calculation *10* (action radius & endurance)
published endurance : 3.00 [hours] with 1 crew and possible useful load : 5.1 [kg] and 88.1 [%] fuel
published range : 324 [km] with 1 crew and 5.1 [kg] useful load and 88.1 [%] fuel
max range theoretically with additional fuel tanks for total 38.3 [litre] fuel : 395.0 [km]
useful load with range 500km : 0 [kg]
production (500 km) : 0 [tonkm/hour]
°
Literature :
http://jn.passieux.free.fr/html/Nieuport.php
Jane’s record breaking aircraft page 25
https://fr.wikipedia.org/wiki/Nieuport_II
Lieutenant Maillols in his Nieuport monoplane. He participated in the Grand semaine d aviation Caen, France 27 July – 02 August 1910 flying a Wright biplane at this occasion.
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 07 October 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4
