Morane Saulnier L Garros | aircraft investigation info

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Morane Saulnier L "Roland Garros"

role : fighter

first flight : operational : April 1915

country : France

design :

production : unknown

general information :

The Morane Saulnier L was used mainly for reconnaissance but due to it’s superior

flying qualities compared to the German Aviatik and Albatros two-seaters the crew

soon started to take light handguns with them, like pistols and carabines. With those

primitive guns they succeeded in downing a score of German aircraft.

The French flyer Roland Garros fitted wedges to the airscrew of his Morane Saulnier

which deflected the bullets fired by a Hotchkiss machine gun. So appeared the first real

fighter aircraft capable of shooting forward through the airscrew.

With his armed MS L Roland Garros succeeded in downing 4 aircraft in the first weeks

of april 1918. Also Brocard and Guynemer used the armed MS L for offensive patrols.

On 7 June 1915 one RNAS MS L , flown by Flight Sub-Lieutenant Reginald Alexander John Warneford of 1 Squadron RNAS intercepted Zeppelin LZ.37, destroying it, the first Zeppelin to be destroyed in the air. Warneford received the Victoria Cross for this achievement.

crew : 1

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

engine : 1 Gnome 7A Monosoupape air-cooled 7 -cylinder Monosoupape rotary engine 80 [hp](58.8 KW)

dimensions :

wingspan : 11.2 [m], length : 6.88 [m], height : 3.93[m]

wing area : 18.3 [m^2]

weights :

max.take-off weight : 650 [kg]

empty weight operational : 393 [kg] bombload : 68 [kg]

performance :

maximum speed : 115 [km/u] op 2000 [m]

climbing speed : 125 [m/min]

service ceiling : 3500 [m]

estimated action radius : 225 [km]

description :

parasol wing with fixed landing gear and tail strut

wingtype : 12 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

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estimated diameter airscrew 2.44 [m]

angle of attack prop : 15.53 [ ]

reduction : 1.00 [ ]

airscrew revs : 1200 [r.p.m.]

pitch at Max speed 1.60 [m]

blade-tip speed at Vmax and max revs. : 157 [m/s]

calculation : *1* (dimensions)

mean wing chord : 1.63 [m]

calculated wing chord (rounded tips): 2.02 [m]

wing aspect ratio : 6.85 []

seize (span*length*height) : 303 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 6.5 [kg/hr]

fuel consumption(cruise speed) : 16.8 [kg/hr] (23.0 [litre/hr]) at 68 [%] power

distance flown for 1 kg fuel : 6.14 [km/kg]

estimated total fuel capacity : 113 [litre] (83 [kg])

calculation : *3* (weight)

weight engine(s) dry : 109.4 [kg] = 1.86 [kg/KW]

weight 39 litre oil tank : 3.3 [kg]

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

oil in engine 0 litre oil : 0.3 [kg]

fuel in engine 0 litre fuel : 0.3 [kg]

weight 10 litre gravity patrol tank(s) : 1.5 [kg]

weight cowling 2.4 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 13.5 [kg]

total weight propulsion system : 128 [kg](19.7 [%])

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fuselage skeleton (wood gauge : 5.51 [cm]): 53 [kg]

bracing : 2.6 [kg]

fuselage covering ( 8.9 [m2] doped linen fabric) : 2.9 [kg]

weight controls + indicators: 5.8 [kg]

weight seats : 3.0 [kg]

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

weight bomb storage : 4.8 [kg]

weight 104 [litre] main fuel tank empty : 8.3 [kg]

weight engine mounts & firewalls : 3 [kg]

total weight fuselage : 89 [kg](13.7 [%])

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weight wing covering (doped linen fabric) : 12 [kg]

total weight ribs (33 ribs) : 39 [kg]

load on front upper spar (clmax) per running metre : 517.1 [N]

load on rear upper spar (vmax) per running metre : 161.7 [N]

total weight 4 spars : 37 [kg]

weight wings : 88 [kg]

weight wing/square meter : 4.78 [kg]

weight cables (45 [m]) : 13.9 [kg] (= 310 [gram] per metre)

diameter cable : 7.1 [mm]

weight fin & rudder (1.5 [m2]) : 7.2 [kg]

weight stabilizer & elevator (2.1 [m2]): 10.0 [kg]

total weight wing surfaces & bracing : 119 [kg] (18.2 [%])

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

weight armament : 12 [kg]

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wheel pressure : 325.0 [kg]

weight 2 wheels (700 [mm] by 82 [mm]) : 14.9 [kg]

weight tailskid : 1.8 [kg]

weight undercarriage with axle 12.7 [kg]

total weight landing gear : 29.4 [kg] (4.5 [%]

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calculated empty weight : 377 [kg](57.9 [%])

weight oil for 5.2 hours flying : 33.8 [kg]

weight 8 strips empty : 0.6 [kg]

weight ammunition (192 rounds) : 7.4 [kg]

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

calculated operational weight empty : 418 [kg] (64.3 [%])

published operational weight empty : 393 [kg] (60.5 [%])

***o***

weight crew : 81 [kg]

weight fuel for 1.5 hours flying : 25 [kg]

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In this picture the machine gun firing trough the airscrew is visible and also that the pilot is sitting in front.

operational weight : 524 [kg](80.6 [%])

bomb load : 68 [kg]

operational weight bombing mission : 592 [kg]

fuel reserve : 58 [kg] enough for 3.43 [hours] flying

possible additional useful load : 0 [kg]

operational weight fully loaded : 650 [kg] with fuel tank filled for 100 [%]

published maximum take-off weight : 650 [kg] (100.0 [%])

I||==|

calculation : * 4 * (engine power)

power loading (operational without bombload) : 8.91 [kg/kW]

total power : 58.8 [kW] at 1200 [r.p.m]

calculation : *5* (loads)

manoeuvre load : 1.5 [g] at 1000 [m]

limit load : 4.5 [g] ultimate load : 6.8 [g] loadfactor : 2.4 [g]

design flight time : 3.48 [hours]

design cycles : 259 sorties, design hours : 900 [hours]

operational wing loading : 281 [N/m^2]

wing stress (3 g) during operation : 176 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.22 ["]

max.angle of attack (stalling angle) : 12.70 ["]

angle of attack at max.speed : 5.43 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° :0.10 [ ]

lift coefficient at max. angle of attack : 1.14 [ ]

lift coefficient at max.speed : 0.55 [ ]

induced drag coefficient at max.speed : 0.0185 [ ]

drag coefficient at max.speed : 0.0789 [ ]

drag coefficient (zero lift) : 0.0603 [ ]

calculation : *8* (speeds

stalling speed at sea-level (OW): 72 [km/u]

landing speed at sea-level (OW without bombload): 86 [km/hr]

min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 87 [km/hr] at 2000 [m] (power:51 [%])

min. power speed (max range) : 87 [km/hr] at 2000 [m] (power:51 [%])

max.rate of climb speed : 77.4 [km/hr] at sea-level

cruising speed : 104 [km/hr] op 2000 [m] (power:62 [%])

design speed prop : 112 [km/hr]

maximum speed : 115 [km/hr] op 2000 [m] (power:75 [%])

climbing speed at sea-level (without bombload) : 175 [m/min]

calculation : *9* (regarding various performances)

take-off distance at sea-level : 311 [m]

lift/drag ratio : 8.18 [ ]

max. practical ceiling : 3775 [m] with flying weight :500 [kg]

practical ceiling (operational weight): 3500 [m] with flying weight :524 [kg]

practical ceiling fully loaded (mtow- 1 hour fuel) : 2225 [m] with flying weight :633 [kg]

published ceiling (3500 [m]

climb to 1500m (without bombload) : 9.92 [min]

max.dive speed : 270.1 [km/hr] at 1225 [m] height

load factor at max.angle turn 1.70 ["g"]

turn radius at 500m: 53 [m]

time needed for 360* turn 12.5 [seconds] at 500m

calculation *10* (action radius & endurance)

operational endurance : 4.93 [hours] with 1 crew and 68 [kg] useful (bomb)load

published endurance : 4.35 [hours] with 1 crew and possible useful (bomb) load : 78 [kg]

action radius : 403 [km] with 1 crew and 20[kg] photo camera/radio transmitter

max range theoretically with additional fuel tanks for total 216 [litre] fuel : 975 [km]

useful load with action-radius 250km : 77 [kg]

production : 8.00 [tonkm/hour]

oil and fuel consumption per tonkm : 2.92 [kg]

I °==/

Literature :

Warplanes WOI page 37, 44, 84

Fighters 1914-19 page 79

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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