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weight and performance calculations for the SAML S.2

An almost perfect side view of an Italian S.A.M.L. S.2 bip… | Flickr

SAML S.2

role : multi role combat aircraft

importance : ***

first flight : operational : July 1917

country : Italy

design : Robert Wild

production : S.1 + S.2 : 657 aircraft

general information :

The Societa Aeronautica Meccanica Lombarda at Monza built the German Aviatik B.I

and B.II up to 1916. In 1916 the company produced an own version, powered by a 260

hp FIAT A-12 engine and designated S.I. It had a movable 6.5 mm Revelli machine gun for the observer. From this the S.2 followed with had a more powerful 300 hp FIAT engine, a smaller wingspan and an additional fixed machine gun on the top plane. It saw front-line service with 16 Italian reconnaissance squadrons. It was strongly built, reliable with good handling qualities, and were well liked by the crews who flew them. After WWI the Belgian air force used it as trainer, fitted with dual-controls and operated from Asch air force base.

users : Italy

crew : 2

armament : 1 fixed 6.50 [mm] (0.256 in) FIAT Rivelli machine-gun on top plane

and 1 movable 6.50 [mm] (0.256 in) FIAT Rivelli machine-gun for the observer

engine : 1 FIAT A-12 bis liquid-cooled 6 -cylinder inline engine 300 [hp](220.7 KW)

dimensions :

wingspan : 12.1 [m], length : 8.5 [m], height : 2.98[m]

wing area : 39.0 [m^2]

weights :

max.take-off weight : 1395 [kg]

empty weight operational : 1020 [kg] bombload : 40 [kg]

performance :

maximum speed : 162 [km/hr] at sea-level

service ceiling : 5000 [m]

endurance : 3.0 [hours]

estimated action radius : 219 [km]

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 [ ]

estimated diameter airscrew 2.62 [m]

angle of attack prop : 14.43 [ ]

fine pitch

reduction : 1.00 [ ]

airscrew revs : 1700 [r.p.m.]

S.A.M.L. S2 | Designed by Robert Wild, the SAML S.2 was inte… | Flickr

pitch at Max speed 1.59 [m]

blade-tip speed at Vmax and max revs. : 238 [m/s]

calculation : *1* (dimensions)

mean wing chord : 1.61 [m]

calculated wing chord (rounded tips): 1.79 [m]

wing aspect ratio : 7.51 []

estimated gap : 1.55 [m]

gap/chord : 0.96 [ ]

seize (span*length*height) : 306 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 5.1 [kg/hr]

fuel consumption(cruise speed) : 50.1 [kg/hr] (68.3 [litre/hr]) at 62 [%] power

distance flown for 1 kg fuel : 2.91 [km/kg]

estimated total fuel capacity : 233 [litre] (170 [kg])

calculation : *3* (weight)

weight engine(s) dry : 438.0 [kg] = 1.99 [kg/KW]

weight 26 litre oil tank : 3.3 [kg]

oil tank filled with 1.7 litre oil : 1.5 [kg]

oil in engine 12 litre oil : 11.0 [kg]

fuel in engine 2 litre fuel : 1.1 [kg]

weight 29 litre gravity patrol tank(s) : 2.8 [kg]

weight radiator : 31.6 [kg]

weight exhaust pipes & fuel lines 27.4 [kg]

weight self-starter : 5.4 [kg]

weight cowling 8.8 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 33.1 [kg]

total weight propulsion system : 561 [kg](40.2 [%])

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

fuselage skeleton (wood gauge : 5.86 [cm]): 75 [kg]

bracing : 4.5 [kg]

fuselage covering ( 13.6 [m2] doped linen fabric) : 4.4 [kg]

weight controls + indicators: 6.4 [kg]

weight seats : 6.0 [kg]

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

SAML S 2 Ardpol 72-038

weight bomb storage : 2.8 [kg]

weight bomb sight : 1.0 [kg]

weight 204 [litre] main fuel tank empty : 19.5 [kg]

weight engine mounts & firewalls : 11 [kg]

total weight fuselage : 135 [kg](9.7 [%])

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

weight wing covering (doped linen fabric) : 25 [kg]

total weight ribs (71 ribs) : 83 [kg]

load on front upper spar (clmax) per running metre : 544.1 [N]

load on rear upper spar (vmax) per running metre : 322.3 [N]

total weight 8 spars : 46 [kg]

weight wings : 154 [kg]

weight wing/square meter : 3.94 [kg]

weight 8 interplane struts & cabane : 15.0 [kg]

weight cables (70 [m]) : 5.0 [kg] (= 72 [gram] per metre)

diameter cable : 3.4 [mm]

weight fin & rudder (1.7 [m2]) : 6.9 [kg]

weight stabilizer & elevator (4.4 [m2]): 17.6 [kg]

total weight wing surfaces & bracing : 198 [kg] (14.2 [%])

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

weight machine-gun(s) : 34.0 [kg]

weight pivot mounting mg :6.0 [kg]

weight machine gun-mounting top plane : 1.5 [kg]

weight ammunition magazine(s) :1.5 [kg]

weight armament : 43 [kg]

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

wheel pressure : 697.5 [kg]

weight 2 wheels (820 [mm] by 109 [mm]) : 31.8 [kg]

weight tailskid : 2.0 [kg]

weight undercarriage with axle 18.9 [kg]

total weight landing gear : 52.7 [kg] (3.8 [%]

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

SAML S.2 : Other

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

calculated empty weight : 990 [kg](71.0 [%])

weight oil for 3.6 hours flying : 18.3 [kg]

weight cooling fluids : 45.5 [kg]

weight 1 drums empty : 1.5 [kg]

weight ammunition (800 rounds) : 20.0 [kg]

weight signal pistol with cartridges : 3.6 [kg]

weight automatic pistol with spare magazines : 1.2 [kg]

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

calculated operational weight empty : 1079 [kg] (77.3 [%])

published operational weight empty : 1020 [kg] (73.1 [%])

_____________

| | o | |

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"

weight crew : 162 [kg]

weight fuel for 2.0 hours flying : 100 [kg]

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

operational weight : 1341 [kg](96.1 [%])

bomb load : 40 [kg]

operational weight bombing mission : 1381 [kg]

weight transceiver : 27 [kg]

operational weight FAC RT mission : 1368 [kg]

fuel reserve : 27 [kg] enough for 0.55 [hours] flying

operational weight fully loaded : 1395 [kg] with fuel tank filled for 75 [%]

published maximum take-off weight : 1395 [kg] (100.0 [%])

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calculation : * 4 * (engine power)

power loading (operational without bombload) : 6.08 [kg/kW]

total power : 220.7 [kW] at 1700 [r.p.m]

calculation : *5* (loads)

manoeuvre load : 2.4 [g] at 1000 [m]

limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 1.3 [g]

design flight time : 2.40 [hours]

design cycles : 125 sorties, design hours : 300 [hours]

operational wing loading : 344 [N/m^2]

wing stress (3 g) during operation : 262 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.19 ["]

max. angle of attack (stalling angle) : 12.43 ["]

angle of attack at max. speed : 2.07 ["]

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 : 0.27 [ ]

induced drag coefficient at max. speed : 0.0057 [ ]

drag coefficient at max. speed : 0.0640 [ ]

drag coefficient (zero lift) : 0.0583 [ ]

calculation : *8* (speeds

stalling speed at sea-level (OW): 79 [km/u]

landing speed at sea-level (OW without bombload): 95 [km/hr]

min. drag speed (max endurance) : 102 [km/hr] at 2500 [m](power :40 [%])

min. power speed (max range) : 116 [km/hr] at 2500 [m] (power:44 [%])

max. rate of climb speed : 98.1 [km/hr] at sea-level

cruising speed : 146 [km/hr] op 2500 [m] (power:64 [%])

design speed prop : 154 [km/hr]

maximum speed : 162 [km/hr] op 100 [m] (power:99 [%])

climbing speed at sea-level (without bombload) : 336 [m/min]

calculation : *9* (regarding various performances)

take-off distance at sea-level : 101 [m]

lift/drag ratio : 7.54 [ ]

max. practical ceiling : 5400 [m] with flying weight :1160 [kg]

practical ceiling (operational weight) : 4675 [m] with flying weight :1341 [kg] line 3385

practical ceiling fully loaded (mtow- 1 hour fuel) : 4675 [m] with flying weight :1345 [kg]

published ceiling (5000 [m]

climb to 1500m (without bombload) : 5.04 [min]

climb to 3000m (without bombload) : 12.77 [min]

max. dive speed : 370.5 [km/hr] at 3675 [m] height

load factor at max. angle turn 2.06 ["g"]

turn radius at 500m: 60 [m]

time needed for 360* turn 11.6 [seconds] at 500m

calculation *10* (action radius & endurance)

operational endurance : 2.68 [hours] with 2 crew and 20 [kg] useful load and 78.9 [%] fuel

published endurance : 3.00 [hours] with 2 crew and possible useful (bomb) load : 4 [kg] and 88.1 [%] fuel

action radius : 196 [km] with 2 crew and 20[kg] photo camera or bombload

max range theoretically with additional fuel tanks for total 378 [litre] fuel : 807 [km]

useful load with action-radius 250km : 106 [kg]

production : 15.39 [tonkm/hour]

oil and fuel consumption per tonkm : 3.58 [kg]

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Literature :

Bombers 1914-19 page 53

Praktisch handboek vliegtuigen deel 1 page 225

Wikipedia

Wings of linen

The aerodrome

Jn.passieux

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 23 March 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4