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weight and performance calculations for the Yakolew Yak-42D
***** PRELIMINARY FILE ****
Yakolew Yak-42D
Role : mid-range jet airliner
importance : ***
first flight : 1988 operational : June 1989
country : Russia
NATO reporting name : CLOBBER
design :
production : 105 Yak-42D (total Yak-42 : 185 aircraft)
general information :
Long-range version
primary users : Donbassaero
Accommodation:
flight crew : 2 cabin crew : 3
passengers : seating for 100 in two class : 16 business class and 84 economy class seats ( 32 -in pitch)
high density seating for 120 passengers
engine : 3 Lotarev D-36 turbofan engines of 63.2 [KN](14207.7 [lbf])
dimensions :
wingspan : 34.88 [m], length : 36.38 [m], height : 9.8 [m]
wing area : 150.0 [m^2]
weights :
operating empty weight : 34500 [kg] max. structural payload : 14500 [kg]
Zero Fuel weight (ZFW) : 49000 [kg] max. landing weight (MLW) : 50500 [kg]
max.take-off weight : 57500 [kg]
performance :
Max. operating Mach number (Mmo) : 0.81 [Mach] (900 [km/hr]) at 7600 [m]
normal cruise speed : 820 [km/hr] (Mach 0.76 ) at 10000 [m] (27 [%] power)
service ceiling : 10700 [m]
range with max fuel : 3000 [km] and allowance for 291.1 [km] diversion and 30 [min]
hold
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
tapered multi-cellular wing with flush-riveted stressed skin
with Fowler flaps airfoil : NACA
sweep angle 3/4 chord: 23.0 [°]
engines attached to the tail, landing gear attached to the wings, fueltanks in the wings
construction : all-metal aluminium-alloy stressed-skin construction with pressurized fuselage
fuselage shape : 0
calculation : *1* (dimensions)
measured wing chord : 4.30 [m] at 50% wingspan
mean wing chord : 4.30 [m]
calculated average wing chord tapered wing with rounded tips: 4.28 [m]
wing aspect ratio : 8.11 []
seize (span*length*height) : 12436 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 94.8 [kg/hr]
fuel consumption (econ. cruise speed) : 3361.6 [kg/hr] (4202.1 [litre/hr]) at 27 [%] power
distance flown for 1 kg fuel : 0.24 [km/kg] at 10000 [m] height, sfc : 66.2 [kg/KN/h]
estimated total fuel capacity : 17449 [litre] (13959 [kg])
calculation : *3* (weight)
weight engine(s) dry : 3327.0 [kg] = 17.55 [kg/KN]
weight 467.6 litre oil tank : 39.75 [kg]
oil tank filled with 1.2 litre oil : 1.1 [kg]
oil in engine 31.7 litre oil : 28.4 [kg]
fuel in engine 23.3 litre fuel : 17.06 [kg]
weight fuel lines 17.4 [kg]
weight engine cowling 568.8 [kg]
total weight propulsion system : 4000 [kg](7.0 [%])
***************************************************************
fuselage aluminium frame : 9305 [kg]
typical cabin layout for 100 passengers : economy : pitch : 81 [cm] ( 3+3 ) seating in 17.2 rows
pax density (normal seating) : 0.59 [m2/pax]
high density seating passengers : 120 at 6 -abreast seating in 20.0 rows, pitch 76 [cm]
weight 2 toilets : 28.5 [kg]
weight 5 hand fire extinguisher : 15 [kg]
weight 1 galleys : 58.5 [kg]
weight overhead stowage for hand luggage : 35.0 [kg]
weight 2 closets : 20.0 [kg]
weight 36 windows : 32.8 [kg]
weight 4 overwing emergency exits : 110.9 [kg]
weight lifejackets : 45.0 [kg]
weight oxygen masks & oxygen generators : 65.0 [kg]
weight tail entrance stairs : 95.0 [kg]
weight emergency flare installation : 10 [kg]
weight 2 emergency evacuation slides : 31.7 [kg]
weight 3 entrance/exit doors : 194.1 [kg]
weight 2 freight doors (belly) : 92.4 [kg]
cabin volume (usable), excluding flight deck : 158.66 [m3]
passenger cabin max.width : 3.45 [m] cabin length : 18.98 [m] cabin height : 2.15 [m]
floor area : 59.0 [m2]
pressure difference :0.47 [kg/cm2]
weight rear pressure bulkhead : 181.5 [kg]
weight air pressurization system : 35.2 [kg]
fuselage covering ( 251.7 [m2] duraluminium 3.26 [mm]) : 2165.6 [kg]
weight floor beams : 332.8 [kg]
weight cabin furbishing : 455.2 [kg]
weight cabin floor : 629.0 [kg]
fuselage (sound proof) isolation : 182.4 [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. : 37.0 [kg]
weight APU / engine starter: 31.6 [kg]
weight lighting : 25.0 [kg]
weight electricity generator : 25.0 [kg]
weight controls : 15.1 [kg]
weight seats : 525.0 [kg]
weight air conditioning : 90 [kg]
weight engine mounts : 95 [kg]
total weight fuselage : 14764 [kg](25.7 [%])
***************************************************************
total weight aluminium ribs (683 ribs) : 2050 [kg]
weight fuel tanks empty for total 17449 [litre] fuel : 977 [kg]
weight wing covering (painted aluminium 3.28 [mm]) : 2653 [kg]
total weight aluminium spars (multi-cellular wing structure) : 3433 [kg]
weight wings : 8137 [kg]
weight wing/square meter : 54.24 [kg]
weight rubber de-icing boots : 38.4 [kg]
weight fin & rudder (14.1 [m2]) : 768.1 [kg]
weight stabilizer & elevator (16.9 [m2]): 916.5 [kg]
weight flight control hydraulic servo actuators: 51.2 [kg]
weight fowler flaps (10.2 [m2]) : 281.6 [kg]
total weight wing surfaces & bracing : 11170 [kg] (19.4 [%])
*******************************************************************
Yak 42D Donbassaero interior 6-abreast seating
wheel pressure : 6325.0 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 226 [mm]) : 1105.7 [kg]
weight 2 Dunlop nose wheels : 138.2 [kg]
weight hydraulic wheel-brakes : 49.0 [kg]
weight pneumatic-hydraulic shock absorbers : 65.3 [kg]
weight wheel hydraulic operated retraction system : 710.0 [kg]
weight undercarriage struts with axle 1446.4 [kg]
total weight landing gear : 3514.7 [kg] (6.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 33448 [kg](58.2 [%])
weight oil for 4.4 hours flying : 416.2 [kg]
weight catering : 146.3 [kg]
weight water : 58.5 [kg]
weight crew : 405 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 26 [kg]
operational weight empty : 34500 [kg] (60.0 [%])
********************************************************************
weight 100 passengers : 7700 [kg]
weight luggage : 1600 [kg]
weight cargo : 5200 [kg]
zero fuel weight (ZFW): 49000 [kg](85.2 [%])
weight fuel for landing (0.4 hours flying) : 1500 [kg]
max. landing weight (MLW): 50500 [kg](87.8 [%])
max. fuel weight : 48459 [kg] (84.3 [%])
payload with max fuel : 97 passengers+luggage 9041 [kg]
published maximum take-off weight : 57500 [kg] (100.0 [%])
Business class 4 rows 1-4 (2+2) > 16 seats, Economy class 14 rows 7-20 (3+3) > 84 seats, total : 100 pax
calculation : * 4 * (engine power)
power loading (Take-off) : 303 [kg/KN]
power loading (operational without useful load) : 285 [kg/kN]
power loading (Take-off) 1 PUF: 455 [kg/KN]
max. total take-off power : 189.6 [KN]
calculation : *5* (loads)
manoeuvre load : 7.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 2.93 [hours]
design cycles : 13545 sorties, design hours : 39645 [hours]
operational wing loading : 3527 [N/m^2]
wing stress (3 g) during operation : 195 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.74 ["]
max. angle of attack (stalling angle, clean) : 11.59 ["]
angle of attack at max. speed : 0.64 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.21 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
max. lift coefficient full flaps : 1.42 [ ]
induced drag coefficient at max.speed : 0.0022 [ ]
drag coefficient at max. speed : 0.0241 [ ]
drag coefficient (zero lift) : 0.0219 [ ]
lift/drag ratio at max. speed : 8.52 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 54138 [kg]): 256 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 222 [km/u]
V : 376.06 te laag, Cl > Clmax berekening PR nodig klopt niet meer cl : 1.41 line 216
flying weight (fw) : 48800.0
landing speed at sea-level (normal landing weight : 50398 [kg]): 255 [km/hr]
max. rate of climb speed : 646 [km/hr] at sea-level
max. endurance speed : 376 [km/u] min. fuel/hr : 2217 [kg/hr] at height : 2743 [m]
max. range speed : 694 [km/u] min. fuel consumption : 3.692 [kg/km] at cruise height : 8839 [m]
cruising speed : 820 [km/hr] at 10000 [m] (power:20 [%])
max. operational speed (Mmo) : 900.00 [km/hr] (Mach 0.81 ) at 7600 [m] (power:32.2 [%])
airflow : 393.6 [kg/s]
Note the tail-entrance
speed of thrust jet : 1284 [km/hr]
climbing speed at sea-level (loaded) : 2437 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 2298 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 316.1 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1110 [m]
take-off distance at sea-level over 15 [m] height : 1177 [m]
landing run : 1288 [m]
landing run from 15 [m] : 2189 [m]
lift/drag ratio : 14.80 [ ]
max. theoretical ceiling : 17900 [m] with flying weight :54138 [kg] line 3359
climb to 1000m with max payload : 0.42 [min]
climb to 2000m with max payload : 0.82 [min]
climb to 3000m with max payload : 1.19 [min]
climb to 5000 [m] with max payload : 1.88 [min]
minimum flying speed at 10700 [m] : 529 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:54138 [kg] ) : 17900 [m]
calculation *10* (action radius & endurance)
published range : 3000 [km] with 5 crew and 10701 [kg] useful load and 88.1 [%] fuel
range : 2073 [km] with 14500.0 [kg] max. useful load (60.9 [%] fuel)
range : 3342 [km] with 100.0 passengers with each 16 [kg] luggage and 98.1 [%] fuel
range max. fuel : 3405 [km] with 9040.8 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 334182 [paskm]
max range theoretically with additional fuel tanks total 28750.0 [litre] fuel : 6230 [km]
useful load with range 500km : 20950 [kg]
useful load with range 500km : 100 passengers
production (theor.max load): 17179 [tonkm/hour]
production (useful load): 11890 [tonkm/hour]
production (passengers): 82000 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.201 [kg]
fuel cost per paskm : 0.042 [eur]
crew cost per paskm : 0.007 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 642 [hr]
writing off per paskm : 0.015 [eur]
insurance per paskm : 0.0011 [eur]
maintenance cost per paskm : 0.007 [eur]
direct operating cost per paskm : 0.073 [eur]
direct operating cost per tonkm (max. load): 0.350 [eur]
direct operating cost per tonkm (normal useful load): 0.505 [eur]
Literature :
Air International jan’00 blz.60
YAK-42 PASSENGER www.tayyareci.com
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 27 June 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4
notes :