Aircraft investigation info>>>>>>> HOME PAGE
Type G in Spanish air museum
Morane Saulnier GB
role : two-seat unarmed reconnaissance
first flight : 1912 operational : October 1912
country : France
design : Leon and Robert Morane and Raymond Saulnier
production : ca.200 aircraft
general information :
The GB was most identical to the type H single-seater. For the Turkish army 40 aircraft were build but when the war started these were incorporated in the Frans army who ordered 94 aircraft additionally. Roland Garros set a new height height record in 1912 reaching 5610m above Tunis (flying a type H ?)
diam.prop : 2.38m (morane-saulnier monoplane archives diameter = 2.57m !)
petrol capacity : 100 litre oil : 22,7 litre.
Could make looping with a passenger.
Pjotr Nesterov, the man who made the first looping in a Nieuport IVG, flew in WWI in the Russian air force.
On 7 September 1914 the Russian pilot Nesterov tried to shoot down an Austrian Albatros B.II flown by Franz Malina and observer Baron Friedrich von Rosenthal of FLIK 11witho his handgun. When this failed Nesterov decided to ram the enemy plane with his Morane Saulnier G (s/n 281). Probably he only wanted to touch the other plane but his own plane was also severely damaged and both airplanes fell from the sky killing the crew near Zjovkva.
It was the 1st time in history a airplane brought down another aircraft. Unfortunately
he himself also crashed
On 18 march 1915 Alexander Kazakov tried to down an enemy airplane with an
enter hook. When this didn’t work he rammed the enemy plane with his landing gear.
High wing loading was probably a problem designing monoplanes short before WWI.
A bigger wing surface was needed but it was difficult to increase the wing span giving to much bending moment and stress. A biplane could be easily made stiff by rigging the flying and landing wires. Only at the end of the war the first aircraft with internally stiff wings appeared, for example the Fokker D.VIII.
The MS GB had with 16 m^2 the smallest wing surface of all 2-seat aircraft used operational in WWI.
users : France, Russia
crew : 2
armament : no fixed armament
engine : 1 Gnome 7A Monosoupape air-cooled 7 -cylinder Monosoupape rotary engine 80 [hp](58.8 KW)
dimensions :
wingspan : 10.2 [m], length : 6.55 [m], height : 2.75[m]
wing area : 16.0 [m^2]
weights :
max.take-off weight : 645 [kg]
empty weight operational : 370 [kg] bombload : 0 [kg]
performance :
maximum speed : 123 [km/hr] at sea-level
climbing speed : 108 [m/min]
service ceiling : 2600 [m]
estimated endurance : 3.13 [hours]
estimated action radius : 173 [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 :0.62 [ ]
estimated diameter airscrew 2.46 [m]
angle of attack prop : 16.42 [ ]
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.71 [m]
blade-tip speed at Vmax and max revs. : 158 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.57 [m]
calculated wing chord (rounded tips): 1.96 [m]
wing aspect ratio : 6.50 []
gap : 0.00 [m]
gap/chord : 0.00 [ ]
seize (span*length*height) : 184 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.5 [kg/hr]
fuel consumption(cruise speed) : 18.5 [kg/hr] (25.3 [litre/hr]) at 75 [%] power
distance flown for 1 kg fuel : 5.98 [km/kg]
estimated total fuel capacity : 90 [litre] (66 [kg])
calculation : *3* (weight)
weight engine(s) dry : 109.4 [kg] = 1.86 [kg/KW]
weight 29 litre oil tank : 2.4 [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 11 litre gravity patrol tank(s) : 1.6 [kg]
weight cowling 2.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 13.5 [kg]
total weight propulsion system : 128 [kg](19.8 [%])
***************************************************************
fuselage skeleton (wood gauge : 5.66 [cm]): 54 [kg]
bracing : 2.5 [kg]
fuselage covering ( 8.1 [m2] doped linen fabric) : 2.6 [kg]
weight controls + indicators: 5.6 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 79 [litre] main fuel tank empty : 6.3 [kg]
weight engine mounts & firewalls : 3 [kg]
total weight fuselage : 85 [kg](13.2 [%])
***************************************************************
weight wing covering (doped linen fabric) : 10 [kg]
total weight ribs (34 ribs) : 38 [kg]
load on front upper spar (clmax) per running metre : 611.8 [N]
load on rear upper spar (vmax) per running metre : 179.4 [N]
total weight 4 spars : 36 [kg]
weight wings : 85 [kg]
weight wing/square meter : 5.32 [kg]
weight cables (41 [m]) : 12.4 [kg] (= 304 [gram] per metre)
diameter cable : 7.0 [mm]
weight fin & rudder (1.2 [m2]) : 6.6 [kg]
weight stabilizer & elevator (1.8 [m2]): 9.7 [kg]
total weight wing surfaces & bracing : 114 [kg] (17.6 [%])
*******************************************************************
weight armament : 0 [kg]
********************************************************************
wheel pressure : 322.5 [kg]
weight 2 wheels (650 [mm] by 76 [mm]) : 14.5 [kg]
weight tailskid : 1.9 [kg]
weight undercarriage with axle 18.0 [kg]
total weight landing gear : 34.4 [kg] (5.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 361 [kg](56.0 [%])
weight oil for 3.8 hours flying : 24.3 [kg]
*******************************************************************
calculated operational weight empty : 385 [kg] (59.7 [%])
published operational weight empty : 370 [kg] (57.4 [%])
---o---
"
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 37 [kg]
********************************************************************
operational weight : 584 [kg](90.6 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 634 [kg]
weight camera : 20 [kg]
operational weight photo mission : 604 [kg]
Morane G flown by Pjotr Nesterov
fuel reserve : 29 [kg] enough for 1.55 [hours] flying
possible additional useful load : 12 [kg]
operational weight fully loaded : 645 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 645 [kg] (100.0 [%])
||
I||==|
||
calculation : * 4 * (engine power)
power loading (operational without bombload) : 9.93 [kg/kW]
total power : 58.8 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.3 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.6 [g]
design flight time : 2.50 [hours]
design cycles : 499 sorties, design hours : 1250 [hours]
operational wing loading : 370 [N/m^2]
wing stress (3 g) during operation : 209 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.23 ["]
max.angle of attack (stalling angle) : 12.84 ["]
angle of attack at max.speed : 5.01 ["]
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 : 0.51 [ ]
induced drag coefficient at max.speed : 0.0167 [ ]
drag coefficient at max.speed : 0.0923 [ ]
drag coefficient (zero lift) : 0.0756 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 82 [km/u]
landing speed at sea-level (OW without bombload): 98 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 96 [km/hr] at 1300 [m] (power:61 [%])
min. power speed (max range) : 96 [km/hr] at 1300 [m] (power:61 [%])
cruising speed : 111 [km/hr] op 1300 [m] (power:75 [%])
design speed prop : 117 [km/hr]
maximum speed : 123 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 154 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 333 [m]
lift/drag ratio : 7.12 [ ]
max. practical ceiling : 4000 [m] with flying weight :476 [kg]
practical ceiling (operational weight): 2675 [m] with flying weight :584 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2175 [m] with flying weight :626 [kg]
published ceiling (2600 [m]
Russian Morane G
climb to 1500m (without bombload) : 11.73 [min]
max.dive speed : 282.4 [km/hr] at 1175 [m] height
load factor at max.angle turn 1.42 ["g"]
turn radius at 500m: 80 [m]
time needed for 360* turn 17.8 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.58 [hours] with 2 crew and 50 [kg] useful (bomb)load and 72.5 [%] fuel
published endurance : 3.13 [hours] with 2 crew and possible useful (bomb) load : 40 [kg] and 88.1 [%] fuel
action radius : 232 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 244 [litre] fuel : 1068 [km]
useful load with action-radius 250km : 95 [kg]
production : 10.52 [tonkm/hour]
oil and fuel consumption per tonkm : 2.38 [kg]
I--°°=/
°
literature :
Historische vliegtuigen page 72,148
Praktisch handboek vliegtuigen deel 1 page 97
wikepedia
Flight 24 May 1913/20 September 1913/18 April 1914/9 May 1914
Warplanes page 27, 39
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 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.2(32-bit)