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weight and performance calculations for the Nieuport IIG
Nieuport IIG
role : experimental/research/flying trials
importance : ****
first flight : operational : December 1911
country : France
design :
production : unknown
general information :
Version with 70hp Gnome engine.
On 24 December 1911 Armand Gobé set the world distance record at 740 km in 8 hrs
15 mins at Pau with his Nieuport IIG with 70hp Gnome engine.
users : Armand Gobé, Charles Weymann, Emmanuel Helen
crew : 1
engine : 1 Gnome 7 Gamma air-cooled 7 -cylinder atmospheric inlet-valve rotary engine 70 [hp](52.2 KW)
dimensions :
wingspan : 11.0 [m], length : 9.0 [m], height : 2.6[m]
wing area : 20.0 [m^2]
weights :
max.take-off weight : 560 [kg]
empty weight operational : 300 [kg] useful load : 0 [kg]
performance :
maximum speed :133 [km/hr] at sea-level
cruise speed :120 [km/u] op 50 [m]
service ceiling : 650 [m]
range : 740 [km]
estimated endurance : 6.18 [hours]
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 : 18.82 [ ]
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.85 [m]
blade-tip speed at Vmax and max revs. : 149 [m/s]
calculation : *1* (dimensions)
wing chord : 1.89 [m]
mean wing chord : 1.82 [m]
calculated wing chord (rounded tips): 2.13 [m]
wing aspect ratio : 6.05 []
seize (span*length*height) : 257 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 4.7 [kg/hr]
fuel consumption(cruise speed) : 22.1 [kg/hr] (30.2 [litre/hr]) at 86 [%] power
distance flown for 1 kg fuel : 5.41 [km/kg] at 325 [m] cruise height, sfc : 492.6 [kg/kwh]
estimated total fuel capacity : 211.90 [litre] (155.33 [kg])
calculation : *3* (weight)
weight engine(s) dry : 103.4 [kg] = 1.98 [kg/KW]
weight 40.1 litre oil tank : 3.41 [kg]
oil tank filled with 0.4 litre oil : 0.4 [kg]
oil in engine 0.3 litre oil : 0.3 [kg]
fuel in engine 0.4 litre fuel : 0.26 [kg]
weight 12.8 litre gravity patrol tank(s) : 1.9 [kg]
weight cowling 2.1 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 8.9 [kg]
total weight propulsion system : 117 [kg](20.9 [%])
***************************************************************
fuselage skeleton (wood gauge : 3.94 [cm]): 36 [kg]
Au début de l’été 1912, Emmanuel Helen , utilisant un IIG monoplace peint en noir (No 13 de course) et surnommé Le Corbeau par les spectateurs, fut chronométré à 163 km/h durant le Circuit d’Anjou auquel il participait.
bracing : 2.3 [kg]
fuselage covering ( 15.3 [m2] doped linen fabric) : 4.9 [kg]
weight instruments. : 1.1 [kg]
weight controls : 4.9 [kg]
weight seats : 3.0 [kg]
weight 199 [litre] main fuel tank empty : 15.9 [kg]
weight engine mount : 2.6 [kg]
total weight fuselage : 71 [kg](12.6 [%])
***************************************************************
weight wing covering (doped linen fabric) : 16 [kg]
total weight ribs (25 ribs) : 33 [kg]
load on front upper spar (clmax) per running metre : 262.3 [N]
load on rear upper spar (vmax) per running metre : 137.8 [N]
total weight 4 spars : 18 [kg]
weight wings : 68 [kg]
weight wing/square meter : 3.38 [kg]
weight cables (44 [m]) : 6.7 [kg] (= 152 [gram] per metre)
diameter cable : 5.0 [mm]
weight fin & rudder (1.4 [m2]) : 5.0 [kg]
weight stabilizer & elevator (2.2 [m2]): 7.8 [kg]
total weight wing surfaces & bracing : 87 [kg] (15.5 [%])
*******************************************************************
wheel pressure : 280.0 [kg]
weight 2 wheels (540 [mm] by 64 [mm]) : 11.6 [kg]
weight tailskid : 0.9 [kg]
weight undercarriage with axle 10.8 [kg]
total weight landing gear : 23.3 [kg] (4.2 [%]
*******************************************************************
Nieuport IIN of Charles Weymann , Gnome 50 hp, wing area : 23.60 m2 span 11m length : 7m50 height 2m48 weight without pilot : 325 kg
********************************************************************
calculated empty weight : 298 [kg](53.2 [%])
weight oil for 7.4 hours flying : 34.9 [kg]
calculated operational weight empty : 333 [kg] (59.4 [%])
published operational weight empty : 300 [kg] (53.6 [%])
___o___
"
weight crew : 81 [kg]
weight fuel for 1.0 hours flying : 22 [kg]
********************************************************************
operational weight : 436 [kg](77.9 [%])
fuel reserve : 124.0 [kg] enough for 5.60 [hours] flying
operational weight fully loaded : 560 [kg] with fuel tank filled for 94 [%]
published maximum take-off weight : 560 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 10.73 [kg/kW]
power loading (operational without useful load) : 8.35 [kg/kW]
total power : 52.2 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.5 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.4 [g]
design flight time : 4.33 [hours]
design cycles : 62 sorties, design hours : 80 [hours]
operational wing loading : 214 [N/m^2]
wing stress (3 g) during operation : 190 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.26 ["]
max. angle of attack (stalling angle) : 13.02 ["]
angle of attack at max. speed : 1.98 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
lift coefficient at max. speed : 0.26 [ ]
induced drag coefficient at max. speed : 0.0046 [ ]
drag coefficient at max. speed : 0.0516 [ ]
drag coefficient (zero lift) : 0.0470 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 63 [km/u]
stalling speed at sea-level (MTOW): 72 [km/u]
landing speed at sea-level: 74 [km/hr]
min. drag speed (max endurance) : 76 [km/hr] at 325 [m](power :38 [%])
min. power speed (max range) : 85 [km/hr] at 325 [m] (power:42 [%])
max. rate of climb speed : 80.7 [km/hr] at sea-level
cruising speed : 120 [km/hr] op 325 [m] (power:74 [%])
design speed prop : 126 [km/hr]
maximum speed : 133 [km/hr] op 50 [m] (power:99 [%])
climbing speed at sea-level : 234 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 78.8 [km/u]
static prop wash : 75 [km/u]
take-off distance at sea-level : 107 [m]
lift/drag ratio : 8.71 [ ]
max. theoretical ceiling : 5373 [m] with flying weight :421 [kg] line 3370
time to 1000m : 4.99 [min]
time to 2000m : 11.71 [min]
climb to 3000m : 20.39 [min]
published ceiling (650 [m]
practical ceiling (operational weight) : 5098 [m] with flying weight :436 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 3808 [m] with flying weight :549 [kg]
max. dive speed : 296.4 [km/hr] at 2808 [m] height
turning speed at CLmax : 94.1 [km/u] at 50 [m] height
turn radius at 50m: 35 [m]
time needed for 360* turn 8.5 [seconds] at 50m
load factor at max. angle turn 2.20 ["g"]
calculation *10* (action radius & endurance)
estimated endurance : 6.18 [hours] with 1 crew and possible useful load : 9.3 [kg] and 88.1 [%] fuel
published range : 740 [km] with 1 crew and 9.3 [kg] useful load and 88.1 [%] fuel
max range theoretically with additional fuel tanks for total 199.4 [litre] fuel : 790.2 [km]
useful load with range 500km : 54 [kg]
production : 6.42 [tonkm/hour]
oil and fuel consumption per tonkm : 4.18 [kg]
°
Literature :
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 07 October 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4
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