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weight and performance calculations for the Morane-Saulnier AI
Morane-Saulnier AI
role : fighter
importance : ***
first flight : operational : January 1918
country : France
design :
production : 1210 aircraft
general information :
Variants MoS 27 (1 Vickers gun), MoS 29 (2 Vickers guns)
1210 aircraft were built but they were withdrawn from the front after a few months,
as it was found to be underpowered and it suffered from structural weakness.
chord : 2.01m
users : France
crew : 1
armament : 2 synchronized 7.70 [mm] (0.303 in) Vickers machine-guns
engine : 1 Gnome 9N Monosoupape air-cooled 9 -cylinder Monosoupape rotary engine
160 [hp](117.7 KW)
dimensions :
wingspan : 8.5 [m], length : 5.63 [m], height : 2.41[m]
wing area : 13.39 [m^2]
weights :
max.take-off weight : 650 [kg]
empty weight operational : 421 [kg] bombload : 0 [kg]
performance :
maximum speed : 208 [km/u] op 2000 [m]
climbing speed : 498 [m/min]
service ceiling : 6200 [m]
endurance : 2.5 [hours]
estimated action radius : 234 [km]
description :
parasol wing 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 :0.64 [ ]
estimated diameter airscrew 2.53 [m]
angle of attack prop : 23.31 [ ]
reduction : 1.00 [ ]
airscrew revs : 1350 [r.p.m.]
pitch at Max speed 2.57 [m]
blade-tip speed at Vmax and max revs. : 188 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.58 [m]
calculated wing chord (rounded tips): 2.05 [m]
wing aspect ratio : 5.40 []
gap : 0.00 [m]
gap/chord : 0.00 [ ]
seize (span*length*height) : 115 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 10.2 [kg/hr]
fuel consumption(cruise speed) : 27.9 [kg/hr] (38.1 [litre/hr]) at 70 [%] power
distance flown for 1 kg fuel : 6.70 [km/kg]
estimated total fuel capacity : 108 [litre] (79 [kg])
calculation : *3* (weight)
weight engine(s) dry : 154.0 [kg] = 1.31 [kg/KW]
weight 37 litre oil tank : 4.7 [kg]
oil tank filled with 0.9 litre oil : 0.8 [kg]
oil in engine 1 litre oil : 0.6 [kg]
fuel in engine 1 litre fuel : 0.6 [kg]
weight 16 litre gravity patrol tank(s) : 1.6 [kg]
weight cowling 4.7 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 181 [kg](27.9 [%])
***************************************************************
Morane monoplane monoplace pursuit airplane
fuselage skeleton (wood gauge : 4.91 [cm]): 35 [kg]
bracing : 1.4 [kg]
fuselage covering ( 6.0 [m2] doped linen fabric) : 1.9 [kg]
weight controls + indicators: 5.2 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 92 [litre] main fuel tank empty : 8.8 [kg]
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 66 [kg](10.1 [%])
***************************************************************
weight wing covering (doped linen fabric) : 9 [kg]
total weight ribs (34 ribs) : 39 [kg]
load on front upper spar (clmax) per running metre : 557.6 [N]
load on rear upper spar (vmax) per running metre : 219.7 [N]
total weight 4 spars : 23 [kg]
weight wings : 70 [kg]
weight wing/square meter : 5.25 [kg]
weight cables (34 [m]) : 6.5 [kg] (= 192 [gram] per metre)
diameter cable : 5.6 [mm]
weight fin & rudder (0.8 [m2]) : 4.5 [kg]
weight stabilizer & elevator (1.5 [m2]): 8.0 [kg]
total weight wing surfaces & bracing : 89 [kg] (13.7 [%])
*******************************************************************
weight machine-gun(s) : 31.8 [kg]
weight ammunition magazine(s) :2.7 [kg]
weight armament : 37 [kg]
********************************************************************
wheel pressure : 325.0 [kg]
weight 2 wheels (680 [mm] by 80 [mm]) : 14.8 [kg]
weight tailskid : 1.4 [kg]
weight undercarriage with axle 11.9 [kg]
total weight landing gear : 28.1 [kg] (4.3 [%]
*******************************************************************
Av.Morane Monoplan.type : Parasol. Mot.rotatif Chasse.
********************************************************************
calculated empty weight : 401 [kg](61.7 [%])
weight oil for 3.0 hours flying : 30.7 [kg]
weight ammunition (800 rounds) : 21.9 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 459 [kg] (70.6 [%])
published operational weight empty : 421 [kg] (64.8 [%])
***o***
"
weight crew : 81 [kg]
weight fuel for 1.5 hours flying : 42 [kg]
********************************************************************
operational weight : 582 [kg](89.5 [%])
estimated bomb load : 25 [kg]
operational weight bombing mission : 607 [kg]
fuel reserve : 37 [kg] enough for 1.34 [hours] flying
possible additional useful load : 6 [kg]
operational weight fully loaded : 650 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 650 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 4.94 [kg/kW]
total power : 117.7 [kW] at 1350 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.0 [g] at 1000 [m]
limit load : 4.5 [g] ultimate load : 6.8 [g] load factor : 1.9 [g]
design flight time : 2.00 [hours]
design cycles : 215 sorties, design hours : 430 [hours]
operational wing loading : 426 [N/m^2]
wing stress (3 g) during operation : 243 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.31 ["]
max. angle of attack (stalling angle) : 13.26 ["]
angle of attack at max. speed : 2.01 ["]
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 : 0.25 [ ]
induced drag coefficient at max. speed : 0.0051 [ ]
drag coefficient at max. speed : 0.0537 [ ]
drag coefficient (zero lift) : 0.0486 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 90 [km/u]
landing speed at sea-level (OW without bombload): 108 [km/hr]
min. drag speed (max endurance) : 125 [km/hr] at 3100 [m](power :38 [%])
min. power speed (max range) : 140 [km/hr] at 3100 [m] (power:41 [%])
max. rate of climb speed : 121.0 [km/hr] at sea-level
cruising speed : 187 [km/hr] op 3100 [m] (power:66 [%])
design speed prop : 202 [km/hr]
maximum speed : 208 [km/hr] op 2000 [m] (power:93 [%])
climbing speed at sea-level (without bombload) : 408 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 221 [m]
lift/drag ratio : 8.08 [ ]
max. practical ceiling : 6525 [m] with flying weight :527 [kg]
practical ceiling (operational weight) : 6050 [m] with flying weight :582 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 5725 [m] with flying weight :622 [kg]
published ceiling (6200 [m]
climb to 1500m (without bombload) : 3.65 [min]
climb to 3000m (without bombload) : 7.75 [min]
max. dive speed : 428.2 [km/hr] at 4725 [m] height
load factor at max. angle turn 2.34 ["g"]
turn radius at 500m: 74 [m]
time needed for 360* turn 11.9 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.84 [hours] with 1 crew and 31 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 2.50 [hours] with 1 crew and possible useful (bomb) load : 40 [kg] and 88.1 [%] fuel
action radius : 303 [km] with 1 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 187 [litre] fuel : 919 [km]
useful load with action-radius 250km : 62 [kg]
production : 11.69 [tonkm/hour]
oil and fuel consumption per tonkm : 3.26 [kg]
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Literature :
Praktisch handboek vliegtuigen deel 1 page 151
Fighters 1914-19 page 78
Jane’s fighting aircraft WWI page 116
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 29 February 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4