Salmson 2A.2
role : multi role combat aircraft
first flight : late 1917 operational : March 1918
country : France
design :
production : 3200 aircraft
general information :
The Salmson 2 was an excellent airplane, it was strong, versatile and had a good armament. It was equipped with the new Salmson
Canton-Unne ' liquid-cooled radial engine.
It had all moving tailplanes.
The Americans employed 705 2A.2’s.
Lt. W.P. Erwin of the 1st sq. van de American
Expeditionary Force shot one day with a Salmson
Eight enemy planes using only the fixed machine gun
Gap : 1.70m petrol capacity : 265 litre, endurance : 3 hrs oil : 47 litre chord : 1.68m
diam. propeller : 2.75m pitch ; 2.10m
calculated pitch angle at ¾ radius is 18°
climb to 2000m : 11 min. To 3000m 17.25 min. to 5000m 40.25 min.
users : France, USA
crew : 2
armament : 1 synchronized 7.70 [mm] (0.303 in) Vickers machine-gun
and 2 movable 7.70 [mm] (0.303 in) Lewis MK.III machine-guns
engine : 1 Salmson Canton-Unne 9Z liquid-cooled 9 -cylinder radial engine 250 [hp](183.9 KW)
dimensions :
wingspan : 11.75 [m], length : 8.5 [m], height : 2.9[m]
wing area : 37.27 [m^2]
weights :
max.take-off weight : 1380 [kg]
empty weight operational : 0 [kg] bombload : 0 [kg]
performance :
maximum speed : 187 [km/hr] at sea-level
climbing speed : 182 [m/min]
service ceiling : 6250 [m]
endurance : 4.51 [hours]
estimated action radius : 380 [km]
Dead French pilot in cockpit of his downed Salmson 2A2
description :
2-bay biplane with fixed landing gear and tail strut
two spar upper and lower 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 [ ]
diameter airscrew 2.75 [m]
angle of attack prop : 18.47 [ ]
reduction : 1.00 [ ]
airscrew revs : 1440 [r.p.m.]
pitch at Max speed 2.16 [m]
blade-tip speed at Vmax and max revs. : 214 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.59 [m]
calculated wing chord (rounded tips): 1.76 [m]
wing aspect ratio : 7.41 []
gap : 1.70 [m]
gap/chord : 1.07 [ ]
seize (span*length*height) : 290 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.4 [kg/hr]
fuel consumption(cruise speed) : 37.9 [kg/hr] (51.8 [litre/hr]) at 62 [%] power
distance flown for 1 kg fuel : 4.43 [km/kg]
estimated total fuel capacity : 265 [litre] (194 [kg])
calculation : *3* (weight)
weight engine(s) dry : 331.0 [kg] = 1.80 [kg/KW]
weight 43 litre oil tank : 3.7 [kg]
oil tank filled with 1.4 litre oil : 1.2 [kg]
oil in engine 10 litre oil : 9.2 [kg]
fuel in engine 1 litre fuel : 0.9 [kg]
weight 22 litre gravity patrol tank(s) : 3.3 [kg]
weight radiator : 26.3 [kg]
weight exhaust pipes & fuel lines 23.8 [kg]
weight self-starter : 4.5 [kg]
weight cowling 7.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 27.6 [kg]
total weight propulsion system : 435 [kg](31.5 [%])
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fuselage skeleton (wood gauge : 5.63 [cm]): 69 [kg]
bracing : 4.1 [kg]
fuselage covering ( 13.6 [m2] doped linen fabric) : 4.4 [kg]
weight controls + indicators: 6.3 [kg]
weight seats : 6.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 243 [litre] main fuel tank empty : 19.4 [kg]
weight oxygen/compressed air flasks for high altitude : 9.8 [kg]
weight engine mounts & firewalls : 9 [kg]
total weight fuselage : 133 [kg](9.7 [%])
***************************************************************
weight wing covering (doped linen fabric) : 24 [kg]
total weight ribs (71 ribs) : 82 [kg]
load on front upper spar (clmax) per running metre : 520.7 [N]
load on rear upper spar (vmax) per running metre : 330.3 [N]
total weight 8 spars : 41 [kg]
weight wings : 147 [kg]
weight wing/square meter : 3.95 [kg]
weight 8 interplane struts & cabane : 19.1 [kg]
weight cables (71 [m]) : 4.6 [kg] (= 65 [gram] per metre)
diameter cable : 3.3 [mm]
weight fin & rudder (1.6 [m2]) : 6.6 [kg]
weight stabilizer & elevator (4.2 [m2]): 16.8 [kg]
total weight wing surfaces & bracing : 194 [kg] (14.1 [%])
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weight machine-gun(s) : 41.9 [kg]
weight pivot mounting mg :6.0 [kg]
weight ammunition magazine(s) :1.8 [kg]
weight synchronizing system : 1.0 [kg]
weight armament : 51 [kg]
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wheel pressure : 690.0 [kg]
weight 2 wheels (750 [mm] by 94 [mm]) : 24.9 [kg]
weight tailskid : 1.9 [kg]
weight undercarriage with axle 21.9 [kg]
total weight landing gear : 48.7 [kg] (3.5 [%]
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calculated empty weight : 862 [kg](62.5 [%])
weight oil for 5.4 hours flying : 34.8 [kg]
weight cooling fluids : 39.7 [kg]
weight 5 drums empty : 2.1 [kg]
weight ammunition (885 rounds) : 32.2 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 974 [kg] (70.6 [%])
estimated operational weight empty : 875 [kg] (63.4 [%])
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weight crew : 162 [kg]
weight (electrical heated) clothing for high altitude : 12.0 [kg]
weight fuel for 2.0 hours flying : 76 [kg]
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operational weight : 1224 [kg](88.7 [%])
estimated bomb load : 50 [kg]
operational weight bombing mission : 1274 [kg]
fuel reserve : 106 [kg] enough for 2.80 [hours] flying
operational weight fully loaded : 1380 [kg] with fuel tank filled for 94 [%]
published maximum take-off weight : 1380 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 6.65 [kg/kW]
total power : 183.9 [kW] at 1440 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.4 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 1.2 [g]
design flight time : 3.16 [hours]
design cycles : 95 sorties, design hours : 300 [hours]
operational wing loading : 322 [N/m^2]
wing stress (3 g) during operation : 245 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.19 ["]
max. angle of attack (stalling angle) : 12.48 ["]
angle of attack at max. speed : 1.15 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max. speed : 0.20 [ ]
induced drag coefficient at max. speed : 0.0030 [ ]
drag coefficient at max. speed : 0.0366 [ ]
drag coefficient (zero lift) : 0.0336 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 77 [km/u]
landing speed at sea-level (OW without bombload): 92 [km/hr]
min. drag speed (max endurance) : 118 [km/hr] at 3125 [m](power :38 [%])
min. power speed (max range) : 127 [km/hr] at 3125 [m] (power:40 [%])
max. rate of climb speed : 112.3 [km/hr] at sea-level
cruising speed : 168 [km/hr] op 3125 [m] (power:61 [%])
design speed prop : 178 [km/hr]
maximum speed : 187 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 315 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 160 [m]
lift/drag ratio : 9.87 [ ]
max. practical ceiling : 7075 [m] with flying weight :1037 [kg]
practical ceiling (operational weight): 6000 [m] with flying weight :1224 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 5350 [m] with flying weight :1342 [kg]
published ceiling (6250 [m]
climb to 1500m (without bombload) : 5.23 [min]
climb to 3000m (without bombload) : 12.37 [min]
max. dive speed : 459.3 [km/hr] at 4350 [m] height
load factor at max. angle turn 2.17 ["g"]
turn radius at 500m: 55 [m]
time needed for 360* turn 10.8 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 5.12 [hours] with 2 crew and 50 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 4.51 [hours] with 2 crew and possible useful (bomb) load : 73 [kg] and 88.1 [%] fuel
action radius : 497 [km] with 2 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 512 [litre] fuel : 1665 [km]
useful load with action-radius 250km : 263 [kg]
production : 44.19 [tonkm/hour]
oil and fuel consumption per tonkm : 1.00 [kg]
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Literature :
jagdflugzeuge WO I page 42
Bomber 1914-1939
prakt. handb. vliegt. deel 1 page160
Jane's FAWOI page121
Warplanes WW1 page 150
Bombers 1914-19 page 65
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 21 August 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4