AIRCRAFT INVESTIGATION
weight and performance calculations for the Boeing 737-200
***** PRELIMINARY FILE ****
Boeing 737-200
importance : ****
first flight : 8 August 1967 operational : April 1968
country : United States of America
design :
production : 991 aircraft
general information :
Early 737s were equipped with hatrack-type overhead stowage.
Passengers : 97 in 2 class : 24 first & 73 econ., all-econ.: 124 3+3 layout
Lower deck cargo volume : 24.8 m3
Single class arrangements : 115 pax at 34-in (0.86m) pitch, 120 pax at 32-in (0.81m) pitch, 130 at 30-in (0.76m) pitch
primary users : United Airlines
flight crew : 2 cabin crew : 4 passengers : 120
engine : 2 Pratt & Whitney JT8D-9A turbofan engines of 65.0 [KN](14612.3 [lbf])
dimensions :
wingspan : 28.35 [m], length : 30.53 [m], height : 11.28 [m]
wing area : 91.1 [m^2]
weights :
operating empty weight : 27125 [kg] max. structural payload : 15966 [kg]
Zero Fuel weight (ZFW) : 43091 [kg] max. landing weight (MLW) : 46720 [kg]
max.take-off weight : 52390 [kg] weight fuel : 14474 [kg] (18092 [liter])
performance :
Max. operating Mach number (Mmo) : 0.84 [Mach] ( 943 [km/hr]) op 7160 [m]
normal cruise speed : 890 [km/hr] (Mach 0.82 ) op 9150 [m] (36 [%] power)
service ceiling : 11000 [m]
range with max fuel : 4000 [km] and allowance for 416.4 [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: 35.0 [°]
engines and landing gear attached to the wings, fuel tanks in the wings and fuselage
construction : all-metal aluminium-alloy stressed-skin construction with pressurized
fuselage fuselage shape : 0
calculation : *1* (dimensions)
mean wing chord : 3.21 [m]
calculated average wing chord tapered wing with rounded tips: 3.25 [m]
wing aspect ratio : 8.82 []
seize (span*length*height) : 9763 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 13.0 [kg/hr]
fuel consumption (econ. cruise speed) : 2820.6 [kg/hr] (3525.7 [litre/hr]) at 36 [%] power
distance flown for 1 kg fuel : 0.32 [km/kg] at 9150 [m] height, sfc : 61.0 [kg/KN/h]
total fuel capacity : 18092 [litre] (14474 [kg])
calculation : *3* (weight)
weight engine(s) dry : 3200.0 [kg] = 24.62 [kg/KW]
weight 80.8 litre oil tank : 6.87 [kg]
oil tank filled with 0.8 litre oil : 0.7 [kg]
oil in engine 21.7 litre oil : 19.5 [kg]
fuel in engine 16.0 litre fuel : 11.70 [kg]
weight fuel lines 18.1 [kg]
weight engine cowling 390.0 [kg]
total weight propulsion system : 3647 [kg](7.0 [%])
***************************************************************
fuselage aluminium frame : 6157 [kg]
typical cabin layout for 120 passengers : average pitch : 81 [cm] ( 3+3 ) seating in 20.0
rows
pax density (normal seating) : 0.61 [m2/pax]
high density seating passengers : 130 at 6 -abreast seating in 21.7 rows, pitch 76 [cm]
weight 2 toilets : 28.5 [kg]
weight 6 hand fire extinguisher : 18 [kg]
weight 2 galleys : 86.3 [kg]
weight overhead stowage for hand luggage : 42.0 [kg]
weight 2 closets : 12.0 [kg]
weight 42 windows : 37.8 [kg]
weight 2 overwing emergency exits : 6.0 [kg]
weight lifejackets : 54.0 [kg]
weight oxygen masks & oxygen generators : 78.0 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 33.8 [kg]
weight 4 entrance/exit doors : 48.0 [kg]
weight 2 freight doors (belly) : 8.0 [kg]
extra main deck space for freight/mail/luggage etc. : 0.98 [m3]
cabin volume (usable), excluding flight deck : 181.69 [m3]
passenger cabin max. width : 3.52 [m] cabin length : 20.88 [m] cabin height : 2.18 [m]
pressure at cruise height 12192.00 [m] : 0.19 [kg/cm2] cabin pressure : 0.77 [kg/cm2]
weight rear pressure bulkhead : 113.0 [kg]
weight air pressurization system : 40.1 [kg]
fuselage covering ( 267.5 [m2] duraluminium 1.95 [mm]) : 1373.4 [kg]
weight floor beams : 390.4 [kg]
weight cabin furbishing : 561.8 [kg]
weight cabin floor : 912.6 [kg]
fuselage (sound proof) isolation : 193.5 [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: 32.5 [kg]
weight lighting : 30.0 [kg]
weight electricity generator : 30.0 [kg]
weight controls : 12.7 [kg]
weight seats : 630.0 [kg]
weight 9046 [litre] main central fuel tanks empty : 506.6 [kg]
weight air conditioning : 180 [kg]
total weight fuselage : 11446 [kg](21.8 [%])
***************************************************************
total weight aluminium ribs (833 ribs) : 1868 [kg]
weight engine mounts : 65 [kg]
weight fuel tanks empty for total 9046 [litre] fuel : 507 [kg]
weight wing covering (painted aluminium 4.05 [mm]) : 1993 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2326 [kg]
weight wings : 6186 [kg]
weight wing/square meter : 67.91 [kg]
weight rubber de-icing boots : 31.2 [kg]
weight fin & rudder (9.3 [m2]) : 634.9 [kg]
weight stabilizer & elevator (10.2 [m2]): 696.7 [kg]
weight flight control hydraulic servo actuators: 42.3 [kg]
weight fowler flaps (5.6 [m2]) : 196.9 [kg]
total weight wing surfaces & bracing : 8360 [kg] (16.0 [%])
*******************************************************************
wheel pressure : 11525.8 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 226 [mm]) : 678.8 [kg]
weight 2 Dunlop nose wheels : 169.7 [kg]
weight hydraulic wheel-brakes : 43.1 [kg]
weight pneumatic-hydraulic shock absorbers : 57.5 [kg]
weight wheel hydraulic operated retraction system : 565.7 [kg]
weight undercarriage struts with axle 1285.5 [kg]
total weight landing gear : 2800.3 [kg] (5.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 26254 [kg](50.1 [%])
weight oil for 5.4 hours flying : 70.1 [kg]
weight catering : 215.7 [kg]
weight water : 86.3 [kg]
weight crew : 486 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 13 [kg]
operational weight empty : 27125 [kg] (51.8 [%])
********************************************************************
weight 120 passengers : 9240 [kg]
weight luggage : 1464 [kg]
weight cargo : 5262 [kg]
zero fuel weight (ZFW): 43091 [kg](82.3 [%])
weight fuel for landing (1.3 hours flying) : 3629 [kg]
max. landing weight (MLW) : 46720 [kg](89.2 [%])
max. fuel weight : 41599 [kg] (79.4 [%])
payload with max fuel : 121 passengers+luggage 10791 [kg]
published maximum take-off weight : 52390 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 403 [kg/KN]
power loading (operational without useful load) : 381 [kg/kN]
power loading (Take-off) 1 PUF: 806 [kg/KN]
max. total take-off power : 130.0 [KN]
calculation : *5* (loads)
manoeuvre load : 6.9 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.3 [g]
design flight time : 3.60 [hours]
design cycles : 5742 sorties, design hours : 20644 [hours]
operational wing loading : 5326 [N/m^2]
wing stress (3 g) during operation : 235 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.72 ["]
max. angle of attack (stalling angle, clean) : 13.36 ["]
angle of attack at max. speed : 1.36 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.27 [ ]
lift coefficient at max. angle of attack : 1.32 [ ]
max. lift coefficient full flaps : 1.59 [ ]
induced drag coefficient at max.speed : 0.0035 [ ]
drag coefficient at max. speed : 0.0294 [ ]
drag coefficient (zero lift) : 0.0259 [ ]
lift/drag ratio at max. speed : 9.14 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 49569 [kg]): 293 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 259 [km/u]
landing speed at sea-level (normal landing weight : 46569 [kg]): 297 [km/hr]
max. rate of climb speed : 639 [km/hr] at sea-level
max. endurance speed : 614 [km/u] min. fuel/hr : 1917 [kg/hr] at height : 9144 [m]
max. range speed : 808 [km/u] min. fuel consumption : 2.740 [kg/km] at cruise height :
9144 [m]
cruising speed : 890 [km/hr] at 9150 [m] (power:29 [%])
max. operational speed (Mmo) : 943.00 [km/hr] (Mach 0.84 ) at 7160 [m] (power:39.9 [%])
airflow : 177.9 [kg/s]
speed of thrust jet : 1826 [km/hr]
climbing speed at sea-level (loaded) : 1708 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 1570 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 361.2 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2004 [m]
take-off distance at sea-level over 15 [m] height : 2097 [m]
landing run : 1741 [m]
landing run from 15 [m] : 2791 [m]
lift/drag ratio : 14.09 [ ]
max. theoretical ceiling : 16900 [m] with flying weight :49569 [kg] line 3359
climb to 1000m with max payload : 0.60 [min]
climb to 2000m with max payload : 1.16 [min]
Aloha airlines 737-200 interior
climb to 3000m with max payload : 1.70 [min]
climb to 5000 [m] with max payload : 2.67 [min]
minimum flying speed at 11000 [m] : 618 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:49569 [kg] ) : 16900 [m]
calculation *10* (action radius & endurance)
published range : 4000 [km] with 6 crew and 12588 [kg] useful load and 95.6 [%] fuel
range : 2934 [km] with 6 crew and 15966.0 [kg] useful load and 70.1 [%] fuel
range max. fuel : 4184 [km] with 120 passengers with each 12.2 [kg] luggage
and 1300 [kg] cargo and 100 [%] fuel
range : 4306 [km] with 130 passengers with each 12.2 [kg] luggage and 102.9 [%] fuel
Available Seat Kilometres (ASK) : 502135 [paskm]
max range theoretically with additional fuel tanks total 31581.2 [litre] fuel : 9220 [km]
useful load with range 500km : 23680 [kg]
useful load with range 500km : 120 passengers
production (theor.max load): 21076 [tonkm/hour]
production (useful load): 14210 [tonkm/hour]
production (passengers): 106800 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.134 [kg]
fuel cost per paskm : 0.027 [eur]
crew cost per paskm : 0.007 [eur]
time between engine failure : 932 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
737-200 C-GWJO cockpit
writing off per paskm : 0.010 [eur]
insurance per paskm : 0.0006 [eur]
maintenance cost per paskm : 0.007 [eur]
direct operating cost per paskm : 0.051 [eur]
direct operating cost per tonkm (max. load): 0.260 [eur]
direct operating cost per tonkm (normal useful load): 0.385 [eur]
Literature :
Front Matter Template 5.0 (boeing.com)
http://www.aircraftmonitor.com/uploads/1/5/9/9/15993320/aircraft_payload_range_analysis_for_financiers___v2.pdf
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