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Morane Saulnier N (MoS.6)

role : fighter

first flight : 22 July 1914 operational : May 1915

country : France

design :

production : 49 aircraft

general information :

The Morane Saulnier type N was just as the type L fitted with a machine gun and wedges on the propeller to deflect the bullets. It was well streamlined, fast and agile. It was not as popular as its predecessors because it was difficult to fly. Control was trough wing warping and it had a high landing speed. Only a good pilot could fly it to its max. It was developed before WWI as racing aircraft. At first it was used unarmed till it was fitted with a machine gun in the spring of 1915. The big "casserole" spinner was good for aerodynamics but prevented the proper cooling of the rotary engine and was removed in 1915. Famous aces like Jean Navarre and Adolphe Pegoud scored there first victories with the type N.

users : France, RFC (60 sq.)

crew : 1

armament : 1 fixed 8.00 [mm] (0.315 in) Hotchkiss M1909 machine-gun firing through the propeller

engine : 1 Le Rhone 9c air-cooled 9 -cylinder two-valve rotary engine 90 [hp](66.2 KW)

On this picture the 24-round ammo strips are clearly visible. After 24 shots the pilot had to reload the machine gun with a new strip.

dimensions :

wingspan : 8.15 [m], length : 5.83 [m], height : 2.5[m]

wing area : 11.0 [m^2]

weights :

max.take-off weight : 450 [kg]

empty weight operational : 288 [kg] bombload : 0 [kg]

performance :

maximum speed : 144 [km/hr] at sea-level

climbing speed : 200 [m/min]

service ceiling : 4000 [m]

endurance : 1.5 [hours]

estimated action radius : 97 [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 :0.53 [ ]

wedges on the airscrew to deflect the bullets, lower prop efficiency

estimated diameter airscrew 2.29 [m]

angle of attack prop : 18.89 [ ]

reduction : 1.00 [ ]

airscrew revs : 1300 [r.p.m.]

pitch at Max speed 1.85 [m]

blade-tip speed at Vmax and max revs. : 161 [m/s]

calculation : *1* (dimensions)

mean wing chord : 1.35 [m]

calculated wing chord (rounded tips): 1.74 [m]

wing aspect ratio : 6.04 []

gap : 0.00 [m]

gap/chord : 0.00 [ ]

seize (span*length*height) : 119 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 4.3 [kg/hr]

fuel consumption(cruise speed) : 19.5 [kg/hr] (26.6 [litre/hr]) at 68 [%] power

distance flown for 1 kg fuel : 6.65 [km/kg]

estimated total fuel capacity : 45 [litre] (33 [kg])

calculation : *3* (weight)

weight engine(s) dry : 122.0 [kg] = 1.84 [kg/KW]

weight 10 litre oil tank : 0.9 [kg]

oil tank filled with 0.5 litre oil : 0.4 [kg]

oil in engine 0 litre oil : 0.3 [kg]

fuel in engine 0 litre fuel : 0.3 [kg]

weight 11 litre gravity patrol tank(s) : 1.7 [kg]

weight cowling 2.6 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 15.2 [kg]

total weight propulsion system : 143 [kg](31.7 [%])

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fuselage skeleton (wood gauge : 3.93 [cm]): 23 [kg]

bracing : 0.9 [kg]

fuselage covering ( 6.4 [m2] doped linen fabric) : 2.1 [kg]

weight controls + indicators: 5.2 [kg]

weight seats : 3.0 [kg]

weight other details, lighting set, etc. : 5.1 [kg]

weight 34 [litre] main fuel tank empty : 2.7 [kg]

weight engine mounts & firewalls : 3 [kg]

total weight fuselage : 45 [kg](10.1 [%])

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weight wing covering (doped linen fabric) : 7 [kg]

total weight ribs (27 ribs) : 27 [kg]

load on front upper spar (clmax) per running metre : 376.9 [N]

load on rear upper spar (vmax) per running metre : 160.4 [N]

total weight 4 spars : 14 [kg]

weight wings : 48 [kg]

weight wing/square meter : 4.38 [kg]

weight cables (33 [m]) : 3.9 [kg] (= 120 [gram] per metre)

diameter cable : 4.4 [mm]

weight fin & rudder (0.8 [m2]) : 3.5 [kg]

weight stabilizer & elevator (1.2 [m2]): 3.3 [kg]

total weight wing surfaces & bracing : 59 [kg] (13.1 [%])

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weight machine-gun(s) : 12.0 [kg]

weight armament : 12 [kg]

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wheel pressure : 225.0 [kg]

weight 2 wheels (650 [mm] by 76 [mm]) : 11.6 [kg]

weight tailskid : 0.9 [kg]

weight undercarriage with axle 9.2 [kg]

total weight landing gear : 21.7 [kg] (4.8 [%]

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calculated empty weight : 281 [kg](62.3 [%])

weight oil for 1.8 hours flying : 7.7 [kg]

weight 8 strips empty : 0.6 [kg]

weight ammunition (192 rounds) : 7.4 [kg]

*******************************************************************

calculated operational weight empty : 296 [kg] (65.7 [%])

published operational weight empty : 288 [kg] (64.0 [%])

---o---

"

weight crew : 81 [kg]

weight fuel for 1.5 hours flying : 29 [kg]

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Side view, without spinner and with Vickers machine gun (synchronized ??)

operational weight : 406 [kg](90.2 [%])

estimated bomb load : 25 [kg]

operational weight bombing mission : 431 [kg]

fuel reserve : 4 [kg] enough for 0.20 [hours] flying

possible additional useful load : 15 [kg]

operational weight fully loaded : 450 [kg] with fuel tank filled for 100 [%]

published maximum take-off weight : 450 [kg] (100.0 [%])

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calculation : * 4 * (engine power)

power loading (operational without bombload) : 6.13 [kg/kW]

total power : 66.2 [kW] at 1300 [r.p.m]

calculation : *5* (loads)

manoeuvre load : 1.7 [g] at 1000 [m]

limit load : 3.8 [g] ultimate load : 5.7 [g] load factor : 1.8 [g]

design flight time : 1.20 [hours]

design cycles : 333 sorties, design hours : 400 [hours]

operational wing loading : 362 [N/m^2]

wing stress (3 g) during operation : 248 [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 : 3.44 ["]

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 : 0.37 [ ]

induced drag coefficient at max.speed : 0.0098 [ ]

drag coefficient at max.speed : 0.0817 [ ]

drag coefficient (zero lift) : 0.0719 [ ]

calculation : *8* (speeds

stalling speed at sea-level (OW): 82 [km/u]

landing speed at sea-level (OW without bombload): 99 [km/hr]

min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 100 [km/hr] at 2000 [m] (power:48 [%])

min. power speed (max range) : 100 [km/hr] at 2000 [m] (power:48 [%])

max.rate of climb speed : 90.1 [km/hr] at sea-level

cruising speed : 130 [km/hr] op 2000 [m] (power:69 [%])

design speed prop : 140 [km/hr]

maximum speed : 144 [km/hr] op 100 [m] (power:99 [%])

climbing speed at sea-level (without bombload) : 252 [m/min]

calculation : *9* (regarding various performances)

take-off distance at sea-level : 252 [m]

lift/drag ratio : 7.03 [ ]

max. practical ceiling : 4500 [m] with flying weight :379 [kg]

practical ceiling (operational weight): 4075 [m] with flying weight :406 [kg]

practical ceiling fully loaded (mtow- 1 hour fuel) : 3700 [m] with flying weight :431 [kg]

published ceiling (4000 [m]

climb to 1500m (without bombload) : 6.80 [min]

climb to 3000m (without bombload) : 17.81 [min]

max.dive speed : 301.9 [km/hr] at 2700 [m] height

load factor at max.angle turn 1.79 ["g"]

turn radius at 500m: 67 [m]

time needed for 360* turn 13.5 [seconds] at 500m

calculation *10* (action radius & endurance)

operational endurance : 1.70 [hours] with 1 crew and 40 [kg] useful (bomb)load and 100.0 [%] fuel

published endurance : 1.50 [hours] with 1 crew and possible useful (bomb) load : 44 [kg] and 88.1 [%] fuel

action radius : 177 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload

max range theoretically with additional fuel tanks for total 110 [litre] fuel : 537 [km]

useful load with action-radius 250km : 6 [kg]

production : 0.71 [tonkm/hour]

oil and fuel consumption per tonkm : 33.29 [kg]

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Literature :

jagdflugzeug WO I page 24,25

Prakt. handb. vliegt. deel 1 page130,131

tussen vleugels van linnen page 40,41

Fighters 1914-19 page 82,158,159

Jane’s fighting aircraft WOI page 116f

Gevechtsvliegtuigen 14/18 deel 2 page19,20

Warplanes page 35,37

They fought for the sky page 35

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 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4