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weight and performance calculations for the Focke Wulf Fw.200A Condor
Focke Wulf Fw.200A Condor
role : regional airliner
importance : ***
first flight : 27 July 1937 flown by Kurt Tank operational : July 1938
country : Germany
design : Kurt Tank
production : 14 civil aircraft and 260 military aircraft
general information :
Designed as long range airliner for cross-Atlantic use. It was designed to cruise at
3000m altitude, the max. height possible without a pressurized cabin. Existing
airliners were designed to cruise at 1500m or below.
The V1 prototype had 875 hp P&W Hornet radials , later in production replaced by
BMW 132 engines. The prototype, registered as D-ACON, made several record
flights. On 10-11 August 1938 it flew non-stop from Berlin to New York in 24 hours
56 minutes. Straight distance 6371 km, average ground speed : 255 km/hr. It had a
higher MTOW of 18000 kg to carry the needed fuel (9084 litre / 6540 kg) for the
trip.
DDL was the first operator to use the FW200, starting scheduled services in July
1938.
Became a feared long range reconnaissance airplane in WWII which co-operated
closely with the U-boats and was responsible for many allied ships sunk.
D-2600 “Immelmann III”was the private aircraft of Adolf Hitler.
users : DDL, Lufthansa, Sindicato Condor
(Brazil)
Registrations : OY-DEM “Jutland”, OY-DAM “Dania”, FW200V1 prototype D-ACON “Brandenburg”, D-ACWG “Holstein”, PP-CBI “Abaitara”, PP-CBJ “Aruma”, D-AETA “Westfalen”, D-2600 “Immelman III” (Hitler), D-ACVH “Grenzmark”, D-ARHW “Friesland”, D-AXFO “Pommeren”, D-AMHC “Nordmark”, prototype D-AERE “Saarland”, D-ADHR, FW200KB-1 D-ASHH “Hessen”, D-AMHL, G-AGAY
crew : 4 passengers : 26
powerplant : 4 BMW 132Dc air-cooled 9 -cylinder radial engine 720 [hp](536.9 KW)
normal rating, supercharged engine, low blower, constant power to height : 2600 [m]
and with 780 [hp](581.6 KW) available for take-off
Measured chord at root : 5.14m at 50% span : 3.52m
dimensions :
wingspan : 33.0 [m], length : 23.85 [m], height : 5.45 [m]
wing area : 119.85 [m^2]
weights :
max.take-off weight : 14600 [kg]
empty weight operational : 9200 [kg] useful load : 3200 [kg]
performance :
maximum speed :374 [km/u] op 1000 [m]
cruise speed :355 [km/u] op 1000 [m]
service ceiling : 6700 [m]
range : 1250 [km]
description :
low-winged monoplane with retractable landing gear with tail wheel
tapered wing with split flaps airfoil : Junkers type
engines and landing gear attached to the wings, fuel tanks in the wings
construction : all-metal stressed-skin (duraluminium) airplane
airscrew :
four Hamilton-Standard constant speed full-feathering 2 -bladed tractor airscrews with max. efficiency :0.74 [ ]
diameter airscrew 3.35 [m]
relative pitch (J) : 1.27 [ ]
power loading prop : 160.27 [KW/m]
theoretical pitch without slip : 4.81 [m]
blade angle prop at max.speed : 32.35 [ ]
reduction : 0.62 [ ]
airscrew revs : 1426 [r.p.m.]
aerodynamic pitch at max. continuous speed 4.26 [m]
blade-tip speed at max.continuous speed : 270 [m/s]
propellor noise in flight : 94 [Db]
calculation : *1* (dimensions)
measured wing chord : 3.52 [m] at 50% wingspan
mean wing chord : 3.63 [m]
calculated average wing chord tapered wing with rounded tips: 3.49 [m]
wing aspect ratio : 9.1 []
seize (span*length*height) : 4289 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 17.2 [kg/hr]
fuel consumption(cruise speed) : 568.2 [kg/hr] (775.2 [litre/hr]) at 81 [%] power
distance flown for 1 kg fuel : 0.62 [km/kg] at 3350 [m] height, sfc : 326.8 [kg/kwh]
estimated total fuel capacity : 3098 [litre] (2271 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 2100.0 [kg] = 0.98 [kg/KW]
weight 134.6 litre oil tank : 11.44 [kg]
oil tank filled with 16.1 litre oil : 14.5 [kg]
oil in engine 12.0 litre oil : 10.7 [kg]
fuel in engine 14.6 litre fuel : 10.74 [kg]
weight 329.6 litre gravity patrol tank(s) : 49.4 [kg]
weight Burgess type silencers : 43.0 [kg]
weight NACA cowling 24.1 [kg]
weight variable pitch control : 27.7 [kg]
weight airscrew(s) incl. boss & bolts : 249.6 [kg]
total weight propulsion system : 2513 [kg](17.2 [%])
***************************************************************
fuselage aluminium frame : 1509 [kg]
cabin layout : pitch : 87 [cm] (2+1) seating in 8.7 rows
pax density : 1.51 [m2/pax]
weight toilet : 8 [kg]
weight 2 fire extinguisher : 6 [kg]
weight pantry : 14.6 [kg]
weight garderobe : 13.0 [kg]
weight 19 windows : 17.4 [kg]
weight door : 5.0 [kg]
passenger cabin max.width : 2.41 [m] cabin length : 9.76 [m] cabin height : 1.90 [m]
weight cabin furbishing : 122.5 [kg]
weight cabin floor : 140.8 [kg]
fuselage covering ( 135.1 [m2] duraluminium 2.76 [mm]) : 982.0 [kg]
fuselage (sound proof) isolation : 37.9 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight artificial horizon : 1.1 [kg]
weight instruments. : 8.0 [kg]
weight APU/engine starter : 50 [kg]
weight lighting : 6.5 [kg]
weight electricity generator : 13.8 [kg]
weight controls : 11.6 [kg]
weight seats : 150.0 [kg]
weight air conditioning : 39 [kg]
total weight fuselage : 3091 [kg](21.2 [%])
***************************************************************
total weight aluminium ribs (205 ribs) : 521 [kg]
weight engine mounts : 107 [kg]
PP-CBJ who served with Sindicato Condor in Brazil
weight fuel tanks empty for total 2769 [litre] fuel : 221 [kg]
weight wing covering (painted aluminium 1.01 [mm]) : 655 [kg]
total weight aluminium spars (multi-cellular wing structure) : 750 [kg]
weight wings : 1926 [kg]
weight wing/square meter : 16.07 [kg]
cantilever wing without bracing cables
weight fin & rudder (12.6 [m2]) : 205.0 [kg]
weight stabilizer & elevator (13.5 [m2]): 217.5 [kg]
weight split flap (6.0 [m2]) : 51.1 [kg]
total weight wing surfaces & bracing : 2728 [kg] (18.7 [%])
*******************************************************************
Can only operate from paved runways
wheel pressure : 7300.0 [kg]
weight 2 Dunlop main wheels (1300 [mm] by 260 [mm]) : 347.4 [kg]
weight tailwheel(s) : 5.9 [kg]
weight Bendix wheel-brakes : 12.4 [kg]
weight Dowty shock absorbers : 16.5 [kg]
weight wheel hydraulic operated retraction system : 57.6 [kg]
weight undercarriage with axle 423.8 [kg]
total weight landing gear : 863.6 [kg] (5.9 [%]
*******************************************************************
********************************************************************
calculated empty weight : 9197 [kg](63.0 [%])
weight oil for 4.2 hours flying : 72.6 [kg]
calculated operational weight empty : 9269 [kg] (63.5 [%])
published operational weight empty : 9200 [kg] (63.0 [%])
weight crew : 324 [kg]
weight fuel for 2.0 hours flying : 1136 [kg]
weight catering : 36.6 [kg]
weight water : 14.6 [kg]
********************************************************************
operational weight empty: 10781 [kg](73.8 [%])
weight 26 passengers : 2002 [kg]
weight luggage : 317 [kg]
weight cargo : 881 [kg]
operational weight loaded: 13981 [kg](95.8 [%])
fuel reserve : 619.2 [kg] enough for 1.09 [hours] flying
operational weight fully loaded : 14600 [kg] with fuel tank filled for 77 [%]
published maximum take-off weight : 14600 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 6.80 [kg/kW]
power loading (operational without useful load) : 5.02 [kg/kW]
power loading (Take-off) 1 PUF: 9.06 [kg/kW]
total power : 2147.6 [kW] at 2300 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 4.8 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 2.82 [hours]
design cycles : 4362 sorties, design hours : 12287 [hours]
Adolf Hitler in front of FW200 D-ACVH “Grenzmark”. German Foreign Minister Joachim von Ribbentrop flew with this aircraft in 1939 to Moscow for the non-aggression treaty between Germany and Russia.
operational wing loading : 882 [N/m^2]
wing stress (3 g) during operation : 165 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.91 ["]
max. angle of attack (stalling angle) : 10.83 ["]
angle of attack at max. speed : -0.26 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.17 [ ]
lift coefficient at max. speed : 0.15 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
max.lift coefficient full flaps : 1.23 [ ]
induced drag coefficient at max.speed : 0.0010 [ ]
drag coefficient at max. speed : 0.0230 [ ]
drag coefficient (zero lift) : 0.0220 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 14032 [kg]): 146 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 127 [km/u]
landing speed at sea-level (normal landing weight : 11466 [kg]): 146 [km/hr]
max. rate of climb speed : 150 [km/hr] at sea-level
max. endurance speed : 154 [km/u] min.fuel/hr : 179 [kg/hr] at height : 610 [m]
max. range speed : 231 [km/u] at cruise height : 4267 [m]
cruising speed : 355 [km/hr] at 3350 [m] (power:80 [%])
max. continuous speed : 364.34 [km/hr]
maximum speed : 374 [km/hr] at 1000 [m] (power:111 [%])
climbing speed at sea-level (loaded) : 525 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 349 [m/min]
climbing speed at 1000 [m] with 2 engines out (2xPUF / MTOW) : 160 [m/min]
FW200 D-ACON “Condor” arriving at Floyd Bennet apt , New York after the first non-stop flight from Berlin to New York, 11 August 1938. Flown by captain Alfred Henke . December 1938 D-ACON was lost when power was lost due to a broken fuel line. It ditched in Cavite Bay , Philippines. All 6 on board survived but the aircraft was a write-off. It was on a promotional flight from Berlin via Basra, Karachi and Hanoi to Tokyo.
calculation : *9* (regarding various performances)
take-off speed : 179.2 [km/u]
emergency/TO power : 780 [hp] at 2394 [rpm]
static prop wash : 135 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 397 [m]
take-off distance at sea-level over 15 [m] height : 468 [m]
landing run : 274 [m]
lift/drag ratio : 15.91 [ ]
climb to 1000m with max payload : 2.07 [min]
climb to 2000m with max payload : 4.17 [min]
climb to 3000m with max payload : 6.49 [min]
practical ceiling (operational weight empty 10781 [kg] ) : 9200 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:14316 [kg] ) : 7700 [m]
calculation *10* (action radius & endurance)
published range : 1250 [km] with 4 crew and 3006 [kg] useful load and 88.1 [%] fuel
range : 1129 [km] with 4 crew and 3200.0 [kg] useful load and 79.6 [%] fuel
range : 1679 [km] with 26 passengers with each 12.2 [kg] luggage
Available Seat Kilometres (ASK) : 43658 [paskm]
max range theoretically with additional fuel tanks total 7162.2 [litre] fuel : 4972
[km]
useful load with range 500km : 4450 [kg]
useful load with range 500km : 26 passengers
production (theor.max load): 1580 [tonkm/hour]
production (useful load): 1136 [tonkm/hour]
production (passengers): 9230 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.37 [kg]
fuel cost per paskm : 0.063 [eur]
crew cost per paskm : 0.033 [eur]
DDL FW200 OY-DAM “Dania” was seized by the British on English soil after the invasion of Denmark by the Germans, it served with the BOAC and then with the RAF until damaged beyond repair in 1941
time between engine failure : 371 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
writing off per paskm : 0.067 [eur]
insurance per paskm : 0.003 [eur]
maintenance cost per paskm : 0.174 [eur]
direct operating cost per paskm : 0.341 [eur]
direct operating cost per tonkm (max. load): 1.992 [eur]
direct operating cost per tonkm (normal useful load): 2.770 [eur]
Literature :
Focke-Wulf Fw 200 V1 Archives - This Day in Aviation
Praktisch handboek vliegtuigen deel 5 page 238,239
Piston-engined airliners page
Jane’s all the world aircraft 1938 page 149c
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
Danish FW200, Belgian Savoia-Marchetti SM73 OO-AGZ and Dutch KLM Douglas DC-3 PH-ALU “Uil” all with neutral markings during the phoney war . Soon those countries would be invaded by the Germans. PH-ALU was destroyed during the bombing of Schiphol on 10 May 1940 by German bombers.
(c) B van der Zalm 22 January 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4