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weight and performance calculations for the Convair CV-440
Convair CV-440
role : commuter prop 50
importance : ****
first flight : 16 December 1955 operational : April 1956
country : United States of America
design :
production : 186 aircraft (plus 26 military)
general information :
Same dimensions as the CV-340, but with higher MTOW and useful load.
More powerful R-2800-CB17 engines.
Max. seating for 52 with removing of the forward carry-on luggage compartment.
Additional soundproofing and renewed exhaust giving less noise for better passenger comfort. Optional weather-radar in the nose, recognized by the longer nose.
Econ. Cruise speed : 465 km/hr Max cruise speed : 483 km/hr
Length : 24.13m without radar nose, and 24.84m with radar nose
primary users : Allegheny, North Central, Eastern Airlines, Swissair, Iberia, SAS,
Sabena, Finnair
flight crew : 2 cabin crew : 2 passengers : 52
powerplant : 2 Pratt & Whitney R-2800-CB17 Double Wasp air-cooled 18 -cylinder radial engine 2400 [hp](1789.7 KW)
normal rating, supercharged engine, high blower, constant power to height : 4000 [m]
and with 2500 [hp](1864.2 KW) available for take-off
dimensions :
wingspan : 32.12 [m], length : 24.84 [m], height : 8.58 [m]
wing area : 85.47 [m^2]
weights :
max.take-off weight : 22544 [kg]
empty weight operational : 15110 [kg] useful load : 5250 [kg]
performance :
maximum continuous speed : 547 [km/u] op 4000 [m]
normal cruise speed : 465 [km/u] op 6100 [m] (70 [%] power)
service ceiling : 9150 [m]
range with max fuel : 2600 [km] and allowance for 118.5 [km] diversion and 30 [min]
hold
13 ft 6 in. diam propellor = 4.11 [m], Menasco main gear 38 in. diam. wheels = 96.5 [cm], Menasco nose wheel 29 in. = 74 [cm] 79 ft 2 in. fuselage = 24.13 [m] without radar, 81 ft 6 in = 24.84 [m] with radar nose
description :
low-winged monoplane with retractable landing gear with nose wheel
tapered multi-cellular wing with flush-riveted stressed skin
with Fowler flaps airfoil : NACA
engines and landing gear attached to the wings, fuel tanks in the wings
construction : all-metal aluminium-alloy stressed-skin construction with pressurized
fuselage. fuselage shape : O
airscrew :
two Hamilton Standard constant speed 3 -bladed tractor airscrews
max. efficiency :0.79 [ ]
diameter airscrew 4.11 [m]
relative pitch (J) : 1.98 [ ]
power loading prop : 290.30 [KW/m]
high power loading prop > more bladed prop needed
theoretical pitch without slip : 9.05 [m]
blade angle prop at max.speed : 44.05 [ ]
tip-speed close to speed of sound (above Mach 0.85) > loose of efficiency
reduction : 0.40 [ ]
airscrew revs : 1120 [r.p.m.]
aerodynamic pitch at max. continuous speed 8.14 [m]
blade-tip speed at max.continuous speed : 285 [m/s]
propellor noise in flight : 99 [Db]
calculation : *1* (dimensions)
measured wing chord : 2.63 [m] at 50% wingspan
mean wing chord : 2.66 [m]
calculated average wing chord tapered wing with rounded tips: 2.56 [m]
wing aspect ratio : 12.1 []
seize (span*length*height) : 6846 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 32.2 [kg/hr]
fuel consumption (econ. cruise speed) : 714.1 [kg/hr] (974.2 [litre/hr]) at 70 [%] power
distance flown for 1 kg fuel : 0.65 [km/kg] at 6100 [m] height, sfc : 285.0 [kg/kwh]
estimated total fuel capacity : 6182 [litre] (4532 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 2136.0 [kg] = 0.60 [kg/KW]
weight 330.3 litre oil tank : 28.07 [kg]
oil tank filled with 26.8 litre oil : 24.1 [kg]
oil in engine 19.9 litre oil : 17.9 [kg]
fuel in engine 24.4 litre fuel : 17.90 [kg]
weight 414.2 litre gravity patrol tank(s) : 62.1 [kg]
weight jet stacks : 89.5 [kg]
weight NACA cowling 80.2 [kg]
weight variable pitch control : 20.7 [kg]
weight airscrew(s) incl. boss & bolts : 518.0 [kg]
total weight propulsion system : 2974 [kg](13.2 [%])
***************************************************************
fuselage aluminium frame : 2959 [kg]
typical cabin layout for 52 passengers : pitch : 81 [cm] ( 2+2 ) seating in 13.0 rows
pax density (normal seating) : 0.76 [m2/pax]
high density seating passengers : 60 at 4 -abreast seating in 14.9 rows
weight 1 toilets : 8.1 [kg]
weight 4 hand fire extinguisher : 12 [kg]
weight pantry : 40.7 [kg]
weight 28 windows : 25.2 [kg]
weight 4 emergency exits : 12.0 [kg]
weight oxygen masks & oxygen generators : 33.8 [kg]
weight emergency flare installation : 10 [kg]
weight emergency evacuation slide : 15 [kg]
weight 2 entrance/exit doors : 24.0 [kg]
extra main deck space for freight/mail/luggage etc. : 4.26 [m3]
cabin volume (usable), excluding flight deck : 74.35 [m3]
passenger cabin max.width : 2.68 [m] cabin length : 14.71 [m] cabin height : 2.00 [m]
pressure at cruise height 6100.00 [m] : 0.47 [kg/cm2] cabin pressure : 0.86 [kg/cm2]
weight rear pressure bulkhead : 91.3 [kg]
weight air pressurization system : 19.7 [kg]
fuselage covering ( 147.7 [m2] duraluminium 2.72 [mm]) : 1049.6 [kg]
weight floor beams : 73.0 [kg]
weight cabin furbishing : 199.2 [kg]
weight cabin floor : 293.4 [kg]
fuselage (sound proof) isolation : 57.7 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
weight radio direction finding (RDF) equipment : 5.0 [kg]
weight Sperry Integrated Flight System : 11.0 [kg]
weight artificial horizon : 1.1 [kg]
weight instruments. : 36.0 [kg]
weight APU / engine starter: 89.5 [kg]
weight lighting : 13.0 [kg]
weight electricity generator : 13.0 [kg]
weight controls : 11.7 [kg]
weight seats : 280.0 [kg]
weight air conditioning : 78 [kg]
total weight fuselage : 5383 [kg](23.9 [%])
***************************************************************
total weight aluminium ribs (433 ribs) : 804 [kg]
weight engine mounts : 179 [kg]
weight two 2884 [litre] main fuel tanks empty : 461.4 [kg]
weight wing covering (painted aluminium 2.76 [mm]) : 1272 [kg]
total weight aluminium spars (multi-cellular wing structure) : 1407 [kg]
weight wings : 3482 [kg]
weight wing/square meter : 40.74 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 35.3 [kg]
weight fin & rudder (12.0 [m2]) : 489.7 [kg]
weight stabilizer & elevator (9.6 [m2]): 392.4 [kg]
weight flight control hydraulic servo actuators: 32.6 [kg]
weight fowler flaps (7.1 [m2]) : 151.1 [kg]
total weight wing surfaces & bracing : 5224 [kg] (23.2 [%])
*******************************************************************
wheel pressure : 4959.7 [kg]
weight 4 Dunlop main wheels (96.5 [mm] by 146 [mm]) : 432.3 [kg]
weight 2 Dunlop nose wheels : 108.1 [kg]
weight hydraulic wheel-brakes : 20.4 [kg]
weight pneumatic-hydraulic shock absorbers : 27.1 [kg]
weight wheel hydraulic operated retraction system : 292.6 [kg]
weight undercarriage struts with axle 568.0 [kg]
total weight landing gear : 1448.5 [kg] (6.4 [%]
*******************************************************************
Cockpit of CV-440 LN-KLK
********************************************************************
calculated empty weight : 15029 [kg](66.7 [%])
weight oil for 6.7 hours flying : 216.1 [kg]
calculated operational weight empty : 15245 [kg] (67.6 [%])
published operational weight empty : 15110 [kg] (67.0 [%])
weight crew : 324 [kg]
weight fuel for 2.0 hours flying : 1428 [kg]
weight catering : 101.8 [kg]
weight water : 40.7 [kg]
********************************************************************
operational weight empty: 17140 [kg](76.0 [%])
weight 52 passengers : 4004 [kg]
weight luggage : 634 [kg]
weight cargo : 612 [kg]
operational weight loaded: 22390 [kg](99.3 [%])
fuel reserve : 154.2 [kg] enough for 0.22 [hours] flying
operational weight fully loaded : 22544 [kg] with fuel tank filled for 35 [%]
published maximum take-off weight : 22544 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 6.05 [kg/kW]
power loading (operational without useful load) : 4.79 [kg/kW]
power loading (Take-off) 1 PUF: 12.09 [kg/kW]
max. total take-off power : 3728.5 [kW]
Interior of Finnair CV-440 OH-LRB
calculation : *5* (loads)
manoeuvre load : 4.4 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.9 [g]
design flight time : 3.91 [hours]
design cycles : 9392 sorties, design hours : 36758 [hours]
operational wing loading : 2533 [N/m^2]
wing stress (3 g) during operation : 187 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.71 ["]
max. angle of attack (stalling angle, clean) : 11.64 ["]
max. angle of attack (full flaps) : 10.75 ["]
angle of attack at max. speed : 0.51 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. speed : 0.21 [ ]
lift coefficient at max. angle of attack : 1.25 [ ]
max. lift coefficient full flaps : 1.68 [ ]
induced drag coefficient at max.speed : 0.0015 [ ]
drag coefficient at max. speed : 0.0223 [ ]
drag coefficient (zero lift) : 0.0208 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 21830 [kg]): 206 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 148 [km/u]
V : 208.04 te laag, Cl > Clmax berekening PR nodig klopt niet meer cl : 1.29 line 216
landing speed at sea-level (normal landing weight : 21615 [kg]): 170 [km/hr]
max. rate of climb speed : 210 [km/hr] at sea-level
max. endurance speed : 208 [km/u] min. fuel/hr : 239 [kg/hr] at height : 610 [m]
max. range speed : 375 [km/u] min. fuel consumption : 1.050 [kg/km] at cruise height :
7620 [m]
cruising speed : 465 [km/hr] at 6100 [m] (power:59 [%])
max. continuous speed* : 547.06 [km/hr] at 4000 [m] (power:100 [%])
climbing speed at sea-level (loaded) : 573 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 165 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 231.1 [km/u]
emergency/TO power : 2500 [hp] at 2800 [rpm]
static prop wash : 153 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 904 [m]
take-off distance at sea-level over 15 [m] height : 996 [m]
landing run : 574 [m]
landing run from 15 [m] : 1175 [m]
lift/drag ratio : 18.85 [ ]
climb to 1000m with max payload : 1.80 [min]
climb to 2000m with max payload : 3.63 [min]
climb to 3000m with max payload : 5.49 [min]
climb to 5000 [m] with max payload : 10.45 [min]
practical ceiling (operational weight empty 17140 [kg] ) : 10000 [m]
practical ceiling fully loaded (mtow- 30 min. fuel:22187 [kg] ) : 8700 [m]
calculation *10* (action radius & endurance)
published range : 2600 [km] with 4 crew and 2982.1 [kg] useful load and 88.1 [%] fuel
range : 1123 [km] with 4 crew and 5250.0 [kg] useful load and 38.1 [%] fuel
range : 1521 [km] with 52.0 passengers with each 12.2 [kg] luggage and 51.6 [%] fuel
Available Seat Kilometres (ASK) : 79115 [paskm]
max range theoretically with additional fuel tanks total 9847.0 [litre] fuel : 6871 [km]
useful load with range 500km : 6450 [kg]
useful load with range 500km : 52 passengers
production (theor.max load): 2999 [tonkm/hour]
production (useful load): 2441 [tonkm/hour]
production (passengers): 24180 [paskm/hour]
oil and fuel consumption per tonkm : 0.249 [kg]
fuel cost per paskm : 0.031 [eur]
crew cost per paskm : 0.019 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 7710 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.023 [eur]
insurance per paskm : 0.0002 [eur]
maintenance cost per paskm : 0.065 [eur]
direct operating cost per paskm : 0.138 [eur]
direct operating cost per tonkm (max. load): 1.111 [eur]
direct operating cost per tonkm (normal useful load): 1.365 [eur]
Literature :
Jane’s commercial transport aircraft 85
Praktisch handboek vliegtuigen deel 5 page 50
Piston-engined airliners page 62,63
Verkeersvliegtuigen nu en straks page 22
Verkeersvliegtuigen B van der Klaauw page 26
Verkeersvliegtuigen Moussault page 99
* max. continuous speed : max. level speed maintainable for minimal 30 min.
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 03 April 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4