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weight and performance calculations for the McDonnel Douglas DC-9-15
***** PRELIMINARY FILE ****
McDonnel Douglas DC-9-15
importance : ****
first flight : DC-9-10 : 25 February 1965 operational : April 1966
country : United States of America
design :
production : 56 aircraft (total DC-9 : 976)
general information :
primary users : KLM, Continental
Accommodation:
flight crew : 2 cabin crew : 3
passengers : seating for 83 in all- economy class seats ( 32 -in pitch)
exit limit : 109 passengers
engine : 2 Pratt & Whitney JT8D-1 turbofan engines of 62.27 [KN](13998.6 [lbf])
dimensions :
wingspan : 27.25 [m], length : 31.82 [m], height : 8.35 [m]
wing area : 86.8 [m^2]
weights :
empty weight : 22300 [kg]
operating empty weight : 22300 [kg] max. structural payload : 11266 [kg]
Zero Fuel weight (ZFW) : 33566 [kg] max. landing weight (MLW) : 37059 [kg]
max.take-off weight : 41140 [kg] weight fuel : 11183 [kg] (13979 [liter])
performance :
Max. operating Mach number (Mmo) : 0.82 [Mach] (902 [km/hr]) at 8500 [m]
normal cruise speed : 871 [km/hr] (Mach 0.80 ) at 9150 [m] (29 [%] power)
service ceiling : 10000 [m]
range with max fuel : 2882 [km] and allowance for 268.1 [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: 24.0 [°]
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 : 8
calculation : *1* (dimensions)
measured wing chord : 3.19 [m] at 50% wingspan
mean wing chord : 3.19 [m]
calculated average wing chord tapered wing with rounded tips: 3.20 [m]
wing aspect ratio : 8.55 []
seize (span*length*height) : 7240 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 12.5 [kg/hr]
fuel consumption (econ. cruise speed) : 2977.4 [kg/hr] (3721.8 [litre/hr]) at 29 [%] power
distance flown for 1 kg fuel : 0.29 [km/kg] at 9150 [m] height, sfc : 82.0 [kg/KN/h]
total fuel capacity : 13979 [litre] (11183 [kg])
calculation : *3* (weight)
weight engine(s) dry : 2908.0 [kg] = 23.35 [kg/KN]
weight 57.7 litre oil tank : 4.90 [kg]
oil tank filled with 0.8 litre oil : 0.7 [kg]
oil in engine 20.8 litre oil : 18.7 [kg]
fuel in engine 15.3 litre fuel : 11.21 [kg]
weight fuel lines 14.0 [kg]
weight engine cowling 373.6 [kg]
total weight propulsion system : 3331 [kg](8.1 [%])
***************************************************************
fuselage aluminium frame : 5166 [kg]
typical cabin layout for 83 passengers : economy : pitch : 81 [cm] ( 3+2 ) seating in 16.6 rows
pax density (normal seating) : 0.62 [m2/pax]
high density seating passengers : 103 at 5 -abreast seating in 20.6 rows, pitch 76 [cm]
weight 2 toilets : 23.2 [kg]
weight 4 hand fire extinguisher : 12 [kg]
weight 1 galleys : 61.5 [kg]
weight overhead stowage for hand luggage : 29.0 [kg]
weight 2 closets : 16.6 [kg]
weight 35 windows : 31.7 [kg]
weight 2 overwing emergency exits : 37.1 [kg]
weight lifejackets : 37.4 [kg]
weight oxygen masks & oxygen generators : 54.0 [kg]
weight tail entrance stairs : 83.5 [kg]
weight emergency flare installation : 10 [kg]
weight 1 emergency evacuation slides : 17.3 [kg]
weight 2 entrance/exit doors : 86.5 [kg]
weight 2 freight doors (belly) : 61.8 [kg]
cabin volume (usable), excluding flight deck : 124.36 [m3]
passenger cabin max.width : 3.11 [m] cabin length : 18.31 [m] cabin height : 2.06 [m]
floor area : 51.3 [m2]
pressure difference :0.58 [kg/cm2]
weight rear pressure bulkhead : 101.2 [kg]
weight air pressurization system : 29.3 [kg]
fuselage covering ( 208.9 [m2] duraluminium 2.24 [mm]) : 1228.2 [kg]
weight floor beams : 189.6 [kg]
weight cabin furbishing : 342.4 [kg]
weight cabin floor : 655.1 [kg]
fuselage (sound proof) isolation : 150.8 [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: 31.1 [kg]
weight lighting : 20.8 [kg]
weight electricity generator : 20.8 [kg]
weight controls : 12.9 [kg]
weight seats : 440.0 [kg]
weight air conditioning : 124 [kg]
weight engine mounts : 62 [kg]
total weight fuselage : 9009 [kg](21.9 [%])
***************************************************************
total weight aluminium ribs (660 ribs) : 1467 [kg]
weight fuel tanks empty for total 13979 [litre] fuel : 783 [kg]
weight wing covering (painted aluminium 3.65 [mm]) : 1711 [kg]
total weight aluminium spars (multi-cellular wing structure) : 1694 [kg]
weight wings : 4872 [kg]
weight wing/square meter : 56.13 [kg]
weight rubber de-icing boots : 30.0 [kg]
weight fin & rudder (8.6 [m2]) : 485.1 [kg]
weight stabilizer & elevator (9.8 [m2]): 548.8 [kg]
weight flight control hydraulic servo actuators: 32.3 [kg]
weight fowler flaps (5.8 [m2]) : 169.7 [kg]
total weight wing surfaces & bracing : 6921 [kg] (16.8 [%])
*******************************************************************
wheel pressure : 9050.8 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 226 [mm]) : 746.1 [kg]
weight 2 Dunlop nose wheels : 186.5 [kg]
weight hydraulic wheel-brakes : 33.6 [kg]
weight pneumatic-hydraulic shock absorbers : 44.8 [kg]
weight wheel hydraulic operated retraction system : 484.5 [kg]
weight undercarriage struts with axle 903.0 [kg]
total weight landing gear : 2398.5 [kg] (5.8 [%]
*******************************************************************
********************************************************************
calculated empty weight : 21660 [kg](52.6 [%])
weight oil for 4.0 hours flying : 49.4 [kg]
weight catering : 109.9 [kg]
weight water : 43.9 [kg]
weight crew : 405 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 32 [kg]
operational weight empty : 22300 [kg] (54.2 [%])
********************************************************************
weight 83 passengers : 6391 [kg]
weight luggage : 1328 [kg]
weight cargo : 3547 [kg]
zero fuel weight (ZFW): 33566 [kg](81.6 [%])
weight fuel for landing (1.2 hours flying) : 3493 [kg]
max. landing weight (MLW): 37059 [kg](90.1 [%])
max. fuel weight : 33483 [kg] (81.4 [%])
payload with max fuel : 82 passengers+luggage 7657 [kg]
published maximum take-off weight : 41140 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 330 [kg/KN]
power loading (operational without useful load) : 314 [kg/kN]
power loading (Take-off) 1 PUF: 661 [kg/KN]
max. total take-off power : 124.5 [KN]
calculation : *5* (loads)
manoeuvre load : 7.6 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.4 [g]
design flight time : 2.65 [hours]
design cycles : 7834 sorties, design hours : 20737 [hours]
operational wing loading : 4413 [N/m^2]
wing stress (3 g) during operation : 236 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.73 ["]
max. angle of attack (stalling angle, clean) : 13.44 ["]
angle of attack at max. speed : 1.54 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.28 [ ]
lift coefficient at max. angle of attack : 1.32 [ ]
max. lift coefficient full flaps : 1.59 [ ]
induced drag coefficient at max.speed : 0.0040 [ ]
drag coefficient at max. speed : 0.0296 [ ]
drag coefficient (zero lift) : 0.0255 [ ]
lift/drag ratio at max. speed : 9.61 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 38163 [kg]): 263 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 236 [km/u]
landing speed at sea-level (normal landing weight : 36982 [kg]): 271 [km/hr]
max. rate of climb speed : 640 [km/hr] at sea-level
max. endurance speed : 420 [km/u] min. fuel/hr : 2039 [kg/hr] at height : 3962 [m]
max. range speed : 702 [km/u] min. fuel consumption : 3.355 [kg/km] at cruise height : 8230 [m]
Length 104 ft 4 inch = 31.80m
Cabin length = 18.29m
cruising speed : 871 [km/hr] at 9150 [m] (power:27 [%])
max. operational speed (Mmo) : 902.00 [km/hr] (Mach 0.82 ) at 8500 [m] (power:31.3 [%])
airflow : 181.1 [kg/s]
speed of thrust jet : 1593 [km/hr]
climbing speed at sea-level (loaded) : 2149 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 2006 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 327.8 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1317 [m]
take-off distance at sea-level over 15 [m] height : 1392 [m]
landing run : 1448 [m]
landing run from 15 [m] : 2407 [m]
lift/drag ratio : 14.02 [ ]
max. theoretical ceiling : 17700 [m] with flying weight :38163 [kg] line 3359
climb to 1000m with max payload : 0.47 [min]
climb to 2000m with max payload : 0.92 [min]
climb to 3000m with max payload : 1.34 [min]
climb to 5000 [m] with max payload : 2.10 [min]
minimum flying speed at 10000 [m] : 521 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:38163 [kg] ) : 17700 [m]
KLM PH-DNB
calculation *10* (action radius & endurance)
published range : 2882 [km] with 5 crew and 8988 [kg] useful load and 88.1 [%] fuel
range : 2216 [km] with 11266.0 [kg] max. useful load (67.7 [%] fuel)
range : 3253 [km] with 83.0 passengers with each 16 [kg] luggage and 99.4 [%] fuel
range max. fuel : 3271 [km] with 7656.8 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 270022 [paskm]
max range theoretically with additional fuel tanks total 23550.0 [litre] fuel : 5616 [km]
useful load with range 500km : 17131 [kg]
useful load with range 500km : 83 passengers
production (theor.max load): 14921 [tonkm/hour]
production (useful load): 9813 [tonkm/hour]
production (passengers): 72293 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.200 [kg]
fuel cost per paskm : 0.041 [eur]
crew cost per paskm : 0.008 [eur]
time between engine failure : 1020 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.012 [eur]
insurance per paskm : 0.0010 [eur]
maintenance cost per paskm : 0.006 [eur]
direct operating cost per paskm : 0.069 [eur]
direct operating cost per tonkm (max. load): 0.334 [eur]
direct operating cost per tonkm (normal useful load): 0.508 [eur]
Literature :
McDonnell Douglas DC-9 - Wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
Verkeersvliegtuigen Moussault page
Verkehrsflugzeuge page
Jane’s commercial transport aircraft page
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