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weight and performance calculations for the Caproni Ca.48
Caproni Ca.48
role : multi-engined passenger aircraft
importance : **
first flight : operational : June 1919
first flight : June 1919 operational : not used operational
country : Italy
design :
production : 2 prototypes
general information :
Conversion of Ca.42 WWI bomber into a passenger aircraft. In the passenger cabin there was place for 16 people. On top of the cabin, on the upper deck there was place for 7 people more behind the crew, seated in the open air.
users : only used for promotional flights
crew : 2 passengers : 23
engine : 3 Liberty L-12 liquid-cooled 12 -cylinder V-engine 400 [hp](298.3 KW)
dimensions :
wingspan : 29.9 [m], length : 13.1 [m], height : 6.3[m]
wing area : 200.0 [m^2]
weights :
max.take-off weight : 7200 [kg]
empty weight operational : 4000 [kg] useful load : 2000 [kg]
performance :
maximum speed :140 [km/hr] at sea-level
cruise speed :126 [km/u] op 100 [m]
service ceiling : 3000 [m]
range : 700 [km]
description :
6-bay triplane with fixed underwing 16 -wheel landing gear and tail strut
two spar upper and lower wing
tail supported by two fabric/plywood covered tail booms
2 engines attached to the wings 1 in the fuselage, landing gear attached to the wings
two fuel tanks in the tail booms, one fuel tank in the fuselage
Another impressive Italian participant at the ELTA Amsterdam (01 August 14 September 1919) was the Società di Aviazione Ing Caproni that transferred three aircraft to Amsterdam. The first to arrive was the Caproni Ca.450 (23170) for two crew and six passengers. It landed without any problems on 6 August and stayed only for a short while in Amsterdam. This aircraft was succeeded by the Caproni Ca.57 (12042) and this one had an enclosed cabin for six. It was on display in the exhibition hall and was used a little bit for joy rides. The largest aircraft to arrive after the Handley Page V/1500 was the three-engine triplane Caproni Ca.48 with looked very much like a flying omnibus. Captain Giulio Laureati had flown the aircraft non-stop from Milano/Taliedo across the Alps to Lyon and Paris/Orly. He was grounded by bad weather, but on 25 August it could proceed to Amsterdam, where it arrived after a flight marked by headwinds. But it was impressive sight once the triplane landed on the airfield. Once its roaring 380hp Liberty engines stopped it became pretty silent on the airfield. On board were also two Belgian officers, as well as two engineers and the co-pilot Baldi. In addition a detachment of the Italian Flying Corps dismounted from the aircraft!
airscrew :
two fixed pitch 2 -bladed tractor airscrews and one fixed pitch pusher propellor with max. efficiency :0.64 [ ]
estimated diameter airscrew 2.79 [m]
angle of attack prop : 11.47 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1750 [r.p.m.]
pitch at Max speed 1.33 [m]
blade-tip speed at Vmax and max revs. : 259 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.23 [m]
mean wing chord : 2.23 [m]
calculated wing chord (rounded leading edge tips): 2.25 [m]
wing aspect ratio : 13.41 []
estimated gap : 2.26 [m]
gap/chord : 1.01 [ ]
seize (span*length*height) : 2468 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 12.5 [kg/hr]
fuel consumption(cruise speed) : 225.2 [kg/hr] (307.3 [litre/hr]) at 73 [%] power
distance flown for 1 kg fuel : 0.56 [km/kg] at 1500 [m] cruise height
estimated total fuel capacity : 1937 [litre] (1420 [kg])
calculation : *3* (weight)
weight engine(s) dry : 1149.0 [kg] = 1.28 [kg/KW]
weight 115.4 litre oil tank : 9.81 [kg]
oil tank filled with 6.7 litre oil : 6.0 [kg]
oil in engine 49.8 litre oil : 44.7 [kg]
fuel in engine 6.1 litre fuel : 4.47 [kg]
weight 130.6 litre gravity patrol tank(s) : 19.6 [kg]
weight radiator : 128.2 [kg]
weight exhaust pipes & fuel lines 42.5 [kg]
weight self-starter : 7.3 [kg]
weight cowling 11.9 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 79.4 [kg]
total weight propulsion system : 1493 [kg](20.7 [%])
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tail boom plywood covering (monocoque) : 91 [kg]
fuselage skeleton (wood gauge : 6.14 [cm]): 258 [kg]
cabin layout : pitch : 55 [cm] seating on opposing benches
weight 23.0 windows : 20.70 [kg]
7 passengers on upper deck, 16 passengers on lower deck
passenger cabin width : 1.54 [m] cabin length : 4.40 [m] cabin height : 1.90 [m]
weight cabin furbishing : 36.33 [kg]
weight cabin floor : 62.28 [kg]
bracing : 23.8 [kg]
fuselage covering ( 45.4 [m2] doped linen fabric) : 13.3 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 5.8 [kg]
weight dual controls + indicators: 20.7 [kg]
weight seats : 75.0 [kg]
weight 602 [litre] main fuel tank empty : 48.2 [kg]
additional in each tailboom a 602 [litre] fuel tank empty : 96.4 [kg]
weight air conditioning : 34 [kg]
weight engine mount and firewall : 15 [kg]
total weight fuselage : 712 [kg](9.9 [%])
***************************************************************
weight wing covering (doped linen fabric) : 137 [kg]
total weight ribs (264 ribs) : 428 [kg]
weight engine mounts : 30 [kg]
load on front upper spar (clmax) per running metre : 876.9 [N]
load on rear upper spar (vmax) per running metre : 634.9 [N]
total weight 12 spars : 326 [kg]
weight wings : 891 [kg]
weight wing/square meter : 4.45 [kg]
weight 48 interplane struts & cabane : 238.1 [kg]
weight cables (229 [m]) : 78.3 [kg] (= 342 [gram] per metre)
diameter cable : 7.5 [mm]
weight fin & rudder (10.4 [m2]) : 47.8 [kg]
weight stabilizer & elevator (22.5 [m2]): 101.7 [kg]
total weight wing surfaces & bracing : 1387 [kg] (19.3 [%])
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good soft ground capabilities
wheel pressure : 450.0 [kg]
weight 16 wheels (850 [mm] by 113 [mm]) : 224.1 [kg]
weight tailskid : 4.5 [kg]
weight undercarriage with axle 54.9 [kg]
total weight landing gear : 283.6 [kg] (3.9 [%]
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calculated empty weight : 3876 [kg](53.8 [%])
weight oil for 6.7 hours flying : 83.5 [kg]
weight cooling fluids : 193.3 [kg]
calculated operational weight empty : 4152 [kg] (57.7 [%])
published operational weight empty : 4000 [kg] (55.6 [%])
_____________
" "
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 450 [kg]
********************************************************************
operational weight empty: 4765 [kg](66.2 [%])
weight 23 passengers : 1771 [kg]
weight luggage & freight : 229 [kg]
operational weight loaded: 6765 [kg](66.2 [%])
fuel reserve : 435.2 [kg] enough for 1.93 [hours] flying
operational weight fully loaded : 7200 [kg] with fuel tank filled for 62 [%]
published maximum take-off weight : 7200 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 8.05 [kg/kW]
power loading (operational without useful load) : 5.32 [kg/kW]
power loading (Take-off) 1 PUF: 12.07 [kg/kW]
total power : 894.8 [kW] at 1750 [r.p.m]
On the top deck the passengers had plenty fresh air
calculation : *5* (loads)
manoeuvre load : 2.1 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.0 [g]
design flight time : 3.89 [hours]
design cycles : 597 sorties, design hours : 2320 [hours]
operational wing loading : 234 [N/m^2]
wing stress (3 g) during operation : 157 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.06 ["]
max. angle of attack (stalling angle) : 9.91 ["]
angle of attack at max. speed : 1.64 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.04 [ ]
lift coefficient at max. speed : 0.25 [ ]
induced drag coefficient at max. speed : 0.0028 [ ]
drag coefficient at max. speed : 0.0794 [ ]
drag coefficient (zero lift) : 0.0765 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 6975 [kg]): 84 [km/u]
landing speed at sea-level: 98 [km/hr]
min. drag speed (max endurance) at cruise height : 99 [km/hr] at 1500 [m]
min. power speed (max range) : 99 [km/hr] at 1500 [m] (power:41 [%])
cruising speed : 126 [km/hr] op 1500 [m] (power:73 [%])
design speed prop : 133 [km/hr]
maximum speed : 140 [km/hr] op 100 [m] (power:103 [%])
climbing speed at sea-level : 444 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 101.9 [km/u]
static prop wash : 126 [km/u]
take-off distance at sea-level : 198 [m]
lift/drag ratio : 8.68 [ ]
climb to 1000m with max payload : 4.54 [min]
climb to 2000m with max payload : 10.65 [min]
climb to 3000m with max payload : 18.61 [min]
practical ceiling (operational weight 4765 [kg]) : 6863 [m]
practical ceiling fully loaded (mtow- 30 min.fuel 7087 [kg] ) : 4893 [m]
max. dive speed : 299.2 [km/hr] at 3893 [m] height
turning speed at CLmax : 120.8 [km/u] at 50 [m] height
turn radius at 50m: 40 [m]
time needed for 360* turn 7.5 [seconds] at 50m
load factor at max. angle turn 3.04 ["g"]
calculation *10* (action radius & endurance)
published range : 700 [km] with 2 crew and 1634.4 [kg] useful load and 88.1 [%] fuel
range : 495 [km] with 2 crew and 2000.0 [kg] useful load and 62.4 [%] fuel
range : 495 [km] with 23.0 passengers with each 10 [kg] luggage and 62.3 [%] fuel
Available Seat Kilometers (ASK) : 11383 [paskm]
max range theoretically with additional fuel tanks for total 4047.3 [litre] fuel : 1659.7 [km]
useful load with range 500km : 2073 [kg]
useful load with range 500km : 20 passengers
production (useful load): 261.18 [tonkm/hour]
production (passengers): 2898.00 [paskm/hour]
oil and fuel consumption per tonkm : 0.91 [kg]
oil and fuel consumption per paskm : 0.08 [kg]
fuel cost per paskm : 0.08 [eur]
crew cost per paskm : 0.10 [eur]
time between engine failure : 135 [hr]
low risk for emergency landing, can continue flying with 1 engine out
writing off per paskm : 0.43 [eur]
insurance per paskm : 0.0265 [eur]
rigging cost per paskm : 0.0061 [eur]
maintenance cost per paskm : 0.6484 [eur]
direct operating cost per paskm : 1.29 [eur]
Serious accidents :
Literature :
The civil aircraft of Caproni (1918-1931) (flyblader.com)
Piston-engined airliners page 13
Caproni Ca.48 (flyingmachines.ru)
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/
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(c) B van der Zalm 10 May 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4