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Morane Saulnier H
role : single seat scout
first flight : 1912 operational : September 1912
country : France
design : Leon en Robert Morane en Raymond Saulnier
production : 26 aircraft
general information :
The type H was a single-seater and the type G a two-seater but further they were mostly identical. On 11 December 1912 Roland Garros set a new height record by reaching 5610m over Tunisia.
During the second international aero meeting, held in Wiener Neustadt in June 1913 Roland Garros won the price for the best precision landings flying a type H. The same year, on 23 September 1913 Garros made the first non-stop crossing over the Mediterranean sea. He flew the 750 km from Frejus, south of France to Bizerte, Tunisia in a Type H with an 60 hp engine.
Anthony Fokker used the type H as example/model for his type M.5, later fitted with a synchronized machine gun indicated as E.I, responsible for the Fokker scourge. Also Pfalz built the type H under license, indicated as Pfalz E.I. The Type H was shortly used by the French at the start of WWI but soon replaced.
users : France
crew : 1
armament : no fixed armament
engine : 1 Gnome 7A Monosoupape air-cooled 7 -cylinder Monosoupape rotary engine 80 [hp](58.8 KW)
dimensions :
wingspan : 9.2 [m], length : 6.38 [m], height : 2.26[m]
wing area : 14.0 [m^2]
weights :
max.take-off weight : 444 [kg]
empty weight operational : 300 [kg] bombload : 0 [kg]
performance :
maximum speed : 120 [km/hr] at sea-level
service ceiling : 4500 [m]
estimated action radius : 105 [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 [ ]
diameter airscrew 2.38 [m]
angle of attack prop : 16.55 [ ]
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.67 [m]
blade-tip speed at Vmax and max revs. : 153 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.52 [m]
calculated wing chord (rounded tips): 1.94 [m]
wing aspect ratio : 6.05 []
gap : 0.00 [m]
gap/chord : 0.00 [ ]
seize (span*length*height) : 133 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.5 [kg/hr]
fuel consumption(cruise speed) : 16.3 [kg/hr] (22.2 [litre/hr]) at 65 [%] power
distance flown for 1 kg fuel : 6.64 [km/kg]
estimated total fuel capacity : 49 [litre] (36 [kg])
calculation : *3* (weight)
weight engine(s) dry : 109.4 [kg] = 1.86 [kg/KW]
weight 18 litre oil tank : 1.6 [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 9 litre gravity patrol tank(s) : 1.4 [kg]
weight cowling 2.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 13.5 [kg]
total weight propulsion system : 128 [kg](28.8 [%])
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fuselage skeleton (wood gauge : 4.66 [cm]): 35 [kg]
bracing : 1.6 [kg]
fuselage covering ( 7.7 [m2] doped linen fabric) : 2.5 [kg]
weight controls + indicators: 5.5 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 40 [litre] main fuel tank empty : 3.2 [kg]
weight engine mounts & firewalls : 3 [kg]
total weight fuselage : 59 [kg](13.3 [%])
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weight wing covering (doped linen fabric) : 9 [kg]
total weight ribs (24 ribs) : 26 [kg]
load on front upper spar (clmax) per running metre : 451.5 [N]
load on rear upper spar (vmax) per running metre : 134.9 [N]
total weight 4 spars : 22 [kg]
Type H in the Musee de l’air, Le Bourget, France
weight wings : 57 [kg]
weight wing/square meter : 4.09 [kg]
weight cables (37 [m]) : 6.7 [kg] (= 182 [gram] per metre)
diameter cable : 5.5 [mm]
weight fin & rudder (1.0 [m2]) : 4.2 [kg]
weight stabilizer & elevator (1.6 [m2]): 6.5 [kg]
total weight wing surfaces & bracing : 75 [kg] (16.8 [%])
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weight armament : 0 [kg]
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wheel pressure : 222.0 [kg]
weight 2 wheels (600 [mm] by 71 [mm]) : 11.1 [kg]
weight tailskid : 1.3 [kg]
weight undercarriage with axle 12.5 [kg]
total weight landing gear : 24.9 [kg] (5.6 [%]
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calculated empty weight : 286 [kg](64.5 [%])
weight oil for 2.3 hours flying : 15.1 [kg]
*******************************************************************
calculated operational weight empty : 302 [kg] (67.9 [%])
published operational weight empty : 300 [kg] (67.6 [%])
---o---
"
weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 33 [kg]
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operational weight : 415 [kg](93.5 [%])
estimated bomb load : 25 [kg]
operational weight bombing mission : 440 [kg]
fuel reserve : 3 [kg] enough for 0.21 [hours] flying
possible additional useful load : 1 [kg]
operational weight fully loaded : 444 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 444 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 7.05 [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 : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.5 [g]
design flight time : 1.56 [hours]
design cycles : 611 sorties, design hours : 950 [hours]
operational wing loading : 291 [N/m^2]
wing stress (3 g) during operation : 213 [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 : 4.18 ["]
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 : 0.43 [ ]
induced drag coefficient at max.speed : 0.0131 [ ]
drag coefficient at max.speed : 0.1136 [ ]
drag coefficient (zero lift) : 0.1006 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 74 [km/u]
landing speed at sea-level (OW without bombload): 88 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 91 [km/hr] at 2250 [m] (power:51 [%])
min. power speed (max range) : 91 [km/hr] at 2250 [m] (power:51 [%])
max.rate of climb speed : 74.6 [km/hr] at sea-level
cruising speed : 108 [km/hr] op 2250 [m] (power:67 [%])
design speed prop : 114 [km/hr]
maximum speed : 120 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 262 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 151 [m]
lift/drag ratio : 5.95 [ ]
max. practical ceiling : 4300 [m] with flying weight :391 [kg]
practical ceiling (operational weight): 3925 [m] with flying weight :415 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 3750 [m] with flying weight :428 [kg]
published ceiling (4500 [m]
climb to 1500m (without bombload) : 6.55 [min]
climb to 3000m (without bombload) : 17.40 [min]
max.dive speed : 242.6 [km/hr] at 2750 [m] height
load factor at max.angle turn 1.76 ["g"]
turn radius at 500m: 55 [m]
time needed for 360* turn 12.3 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.21 [hours] with 1 crew and 26 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 1.94 [hours] with 1 crew and possible useful (bomb) load : 30 [kg] and 88.1 [%] fuel
action radius : 138 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 84 [litre] fuel : 408 [km]
useful load with action-radius 250km : 0 [kg]
production (500 km) : 0 [tonkm/hour]
I-°=/
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Literature :
Historische Vliegtuigen blz.148
Jane’s record breaking aircraft blz.29
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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