Nieuport IVG two-seat reconnaissance monoplane weight and performance calculations; added with pictures and facts
Nieuport IVG
role : two-seat unarmed reconnaissance
first flight : 1911 operational : October 1911
country : France
design :
production : 400 aircraft
general information :
Bought by the Italian army who used them in North-Africa. On 24 October 1911 Captain Moizo made the 2nd reconnaissance flight ever carried out by a military aircraft. Later in 1912 Moizo became the first victim of anti aircraft fire when he was shot down by an ancient Austrian canon. The Russians used the IVG the most, they built 300 aircraft under license.
On 27 August 1913 Pyotr Nesterov made the first looping ever. After this feat he was arrested immediately for jeopardizing Russian state property
When his act was also done in France Nesterov was promoted and got a medal. The France equipped an escadrille (N12) with the type. They flew with 10 aircraft at Reims and used it still operational at the beginning of WWI. The number of serviceable aircraft decreased due to war losses.
The IVG used as military 2-seater by France and Italy had an 80 hp Gnome engine. The IVG was used in many countries indicating it was popular and a sound design.
Users : France(10),Italy,Russia(300),RFC(4), Greece, Japan
construction : frame : spruce and steel tubes, mahogany airscrew. covering: strengthened linen
crew : 2
armament : no fixed armament
engine : 1 Gnome 7 Gamma air-cooled 7 -cylinder atmospheric inlet-valve rotary engine 70 [hp](51.5 KW)
dimensions :
wingspan : 11.6 [m], length : 7.8 [m], height : 2.75[m]
wing area : 17.5 [m^2]
weights :
max.take-off weight : 600 [kg]
empty weight operational : 350 [kg] bombload : 0 [kg]
An original IVG can be seen in the Airforce Museum in Malmen, near to Linkoping.
performance :
maximum speed : 105 [km/hr] at sea-level
climbing speed : 100 [m/min]
service ceiling : unknown
endurance : 2.0 [hours]
estimated action radius : 94 [km]
description :
shoulder-winged monoplane with fixed landing gear and tail strut
two spar wing
engines, landing gear, fuel and bombs in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.61 [ ]
estimated diameter airscrew 2.76 [m]
angle of attack prop : 12.64 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.46 [m]
blade-tip speed at Vmax and max revs. : 176 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.51 [m]
calculated wing chord (rounded tips): 1.83 [m]
wing aspect ratio : 7.69 []
gap : 0.00 [m]
gap/chord : 0.00 [ ]
seize (span*length*height) : 249 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 4.6 [kg/hr]
fuel consumption(cruise speed) : 20.1 [kg/hr] (27.4 [litre/hr]) at 78 [%] power
distance flown for 1 kg fuel : 4.71 [km/kg]
estimated total fuel capacity : 62 [litre] (46 [kg])
calculation : *3* (weight)
weight engine(s) dry : 101.9 [kg] = 1.98 [kg/KW]
weight 14 litre oil tank : 1.2 [kg]
oil tank filled with 0.4 litre oil : 0.3 [kg]
oil in engine 0 litre oil : 0.3 [kg]
fuel in engine 0 litre fuel : 0.3 [kg]
weight 12 litre gravity patrol tank(s) : 1.7 [kg]
weight cowling 2.1 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 11.8 [kg]
total weight propulsion system : 118 [kg](19.7 [%])
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fuselage skeleton (wood gauge : 5.09 [cm]): 52 [kg]
bracing : 2.8 [kg]
fuselage covering ( 11.5 [m2] doped linen fabric) : 3.7 [kg]
weight controls + indicators: 6.1 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 51 [litre] main fuel tank empty : 4.0 [kg]
weight engine mounts & firewalls : 3 [kg]
total weight fuselage : 82 [kg](13.7 [%])
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weight wing covering (doped linen fabric) : 11 [kg]
total weight ribs (33 ribs) : 36 [kg]
load on front upper spar (clmax) per running metre : 430.7 [N]
load on rear upper spar (vmax) per running metre : 145.8 [N]
total weight 4 spars : 33 [kg]
weight wings : 80 [kg]
weight wing/square meter : 4.58 [kg]
weight cables (46 [m]) : 12.8 [kg] (= 277 [gram] per metre)
diameter cable : 6.7 [mm]
weight fin & rudder (1.6 [m2]) : 7.4 [kg]
weight stabilizer & elevator (2.0 [m2]): 9.1 [kg]
total weight wing surfaces & bracing : 109 [kg] (18.2 [%])
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weight armament : 0 [kg]
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Can only operate from paved runways
!!! wheel density very high > check weight & dims !!!
wheel pressure : 300.0 [kg]
weight 2 wheels (460 [mm] by 54 [mm]) : 12.2 [kg]
weight tailskid : 1.5 [kg]
weight undercarriage with axle 17.8 [kg]
total weight landing gear : 31.5 [kg] (5.3 [%]
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The first Japanese Army sorties were flown on September 21st 1914 using two Farmans and the Nieuport IVG to drop bombs on German military camps.
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calculated empty weight : 341 [kg](56.9 [%])
weight oil for 2.4 hours flying : 11.1 [kg]
*******************************************************************
calculated operational weight empty : 353 [kg] (58.8 [%])
published operational weight empty : 350 [kg] (58.3 [%])
---o---
"
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 40 [kg]
********************************************************************
operational weight : 555 [kg](92.4 [%])
bombload could not be carried with fuel for 2 hours flying time
weight camera : 20 [kg]
operational weight photo mission : 575 [kg]
fuel reserve : 5 [kg] enough for 0.27 [hours] flying
possible additional useful load : 20 [kg]
operational weight fully loaded : 600 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 600 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 10.77 [kg/kW]
total power : 51.5 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.1 [g] at 1000 [m]
Emmanouel Argyropoulos and Nieuport IV.G Alkyon in which he made the first flight in Greece
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.2 [g]
design flight time : 1.60 [hours]
design cycles : 469 sorties, design hours : 750 [hours]
operational wing loading : 322 [N/m^2]
wing stress (3 g) during operation : 211 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.18 ["]
max.angle of attack (stalling angle) : 12.36 ["]
angle of attack at max.speed : 5.92 ["]
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 : 0.60 [ ]
induced drag coefficient at max.speed : 0.0200 [ ]
drag coefficient at max.speed : 0.1180 [ ]
drag coefficient (zero lift) : 0.0980 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 76 [km/u]
landing speed at sea-level (OW without bombload): 91 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 87 [km/hr] at 1000 [m] (power:66 [%])
min. power speed (max range) : 87 [km/hr] at 1000 [m] (power:66 [%])
cruising speed : 94 [km/hr] op 1000 [m] (power:75 [%])
design speed prop : 100 [km/hr]
maximum speed : 105 [km/hr] op 100 [m] (power:99 [%])
Nieuport IV owned by Claude Grahame-White
climbing speed at sea-level (without bombload) : 141 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 204 [m]
lift/drag ratio : 6.80 [ ]
max. practical ceiling : 3825 [m] with flying weight :444 [kg]
practical ceiling (operational weight): 2375 [m] with flying weight :555 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2075 [m] with flying weight :580 [kg]
published ceiling (0 [m]
climb to 1500m (without bombload) : 13.18 [min]
max.dive speed : 224.9 [km/hr] at 1075 [m] height
load factor at max.angle turn 1.37 ["g"]
turn radius at 500m: 72 [m]
time needed for 360* turn 17.6 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 1.77 [hours] with 2 crew and 50 [kg] useful (bomb)load and 77.9 [%] fuel
published endurance : 2.00 [hours] with 2 crew and possible useful (bomb) load : 45 [kg] and 88.1 [%] fuel
action radius : 154 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 227 [litre] fuel : 784 [km]
useful load with action-radius 250km : 60 [kg]
production : 5.70 [tonkm/hour]
oil and fuel consumption per tonkm : 4.33 [kg]
I--°°=/
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Literature :
Historische vliegtuigen page 70,71,150
Praktisch handboek deel 1 page 97
En.wikepedia.org
Warplanes page 27
wikepedia
Jane’s fighting aircraft WWI page 217f
Flight 11 November 1911
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.
For copyright on drawings/photographs/content please mail to below mail address
(c) B van der Zalm 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.2(32-bit)