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weight and performance calculations for the Curtiss T.32 Condor
Curtiss T.32 Condor
importance : ****
first flight : 30 January 1933 operational : June 1934
country : United States of America
design :
production : 45 aircraft
general information :
Designed to fly with 12 sleeper beds, as a luxury night sleeper transport. During day it
could carry 15 people in the normal way. It was outclassed by the DC-2 and soon it
was replaced on the major routes. Some aircraft were upgraded to AT-32 standard with variable pitch propellors and NACA engine cowlings replacing the Townend rings.
Fuel capacity : 4 x 75 US gallon tanks in the upper wing = 1135 litre
users : Eastern Air Transport, American Airliners
crew : 3 passengers : 15
engine : 2 Wright SR-1820-F2 Cyclone air-cooled 9 -cylinder radial engine 705 [hp] .
(525.7 KW) supercharged engine, constant power to height : 1189 [m]
dimensions :
wingspan : 24.99 [m], length : 14.81 [m], height : 4.98 [m]
wing area : 112.2 [m^2]
weights :
max.take-off weight : 7620 [kg]
empty weight operational : 5085 [kg] useful load : 1500 [kg]
performance :
maximum speed :274 [km/u] op 2400 [m]
cruise speed :260 [km/u] op 2400 [m]
service ceiling : 7011 [m]
range : 866 [km]
description :
2-bay biplane with retractable landing gear with tail wheel
two spar upper and lower wing airfoil : NACA 2412
engines and landing gear attached to the wings, fuel tanks in the wings
construction : fuselage > welded steel tubes covered with canvas, wooden wing covered
with plywood
airscrew :
ground adjustable 3 -bladed metal Smith tractor propeller with max. efficiency :0.73 [ ]
estimated diameter airscrew 2.94 [m]
power loading prop : 119.21 [KW/m]
angle of attack prop : 18.24 [ ]
reduction : 1.00 [ ]
airscrew revs : 2000 [r.p.m.]
pitch at Max speed 2.28 [m]
blade-tip speed at Vmax and max revs. : 317 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.70 [m] at 50% wingspan
mean wing chord : 2.24 [m]
calculated average wing chord tapered wing with rounded tips: 2.44 [m]
wing aspect ratio : 11.13 []
gap : 3.02 [m]
gap/chord : 1.35 [ ]
seize (span*length*height) : 1843 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 14.7 [kg/hr]
fuel consumption(cruise speed) : 220.4 [kg/hr] (300.7 [litre/hr]) at 65 [%] power
distance flown for 1 kg fuel : 1.18 [km/kg] at 3506 [m] height, sfc : 324.6 [kg/kwh]
estimated total fuel capacity : 1135 [litre] (832 [kg])
calculation : *3* (weight)
weight engine(s) dry : 812.0 [kg] = 0.77 [kg/KW]
weight 91.7 litre oil tank : 7.80 [kg]
oil tank filled with 7.9 litre oil : 7.1 [kg]
oil in engine 5.9 litre oil : 5.3 [kg]
fuel in engine 7.2 litre fuel : 5.26 [kg]
weight 127.8 litre gravity patrol tank(s) : 19.2 [kg]
weight starter (E.H.I. - Electric Hand Inertia): 12.9 [kg]
weight Townend ring cowling 23.6 [kg]
weight airscrew(s) incl. boss & bolts : 131.8 [kg]
total weight propulsion system : 1017 [kg](13.3 [%])
***************************************************************
fuselage skeleton (steel tubes) : 9.14 [cm]): 975 [kg]
cabin layout : pitch : 87 [cm] (2+1) seating in 5.0 rows
weight toilet : 8 [kg]
weight 2 fire extinguisher : 6 [kg]
weight pantry : 8.0 [kg]
weight 10 windows : 9.0 [kg]
passenger cabin width : 2.07 [m] cabin length : 4.95 [m] cabin height : 1.90 [m]
weight cabin furbishing : 50.8 [kg]
weight cabin floor : 65.5 [kg]
bracing : 109.4 [kg]
fuselage covering ( 76.8 [m2] doped linen fabric) : 24.0 [kg]
fuselage (sound proof) isolation : 22.5 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight Sperry gyro auto-pilot - course control equipment : 1.5 [kg]
weight instruments. : 6.0 [kg]
weight lighting : 3.8 [kg]
weight electricity generator : 7.6 [kg]
weight controls : 8.2 [kg]
weight seats : 90.0 [kg]
weight air conditioning : 22 [kg]
total weight fuselage : 1393 [kg](18.3 [%])
***************************************************************
weight 5.0 [mm] plywood wing covering : 359 [kg]
total weight wooden ribs (185 ribs) : 453 [kg]
weight engine mounts : 53 [kg]
weight two 504 [litre] main fuel tanks empty : 80.6 [kg]
total weight 8 wooden spars : 573 [kg]
weight wings : 1385 [kg]
weight wing/square meter : 12.35 [kg]
weight 8 interplane struts & cabane : 313.1 [kg]
weight cables (139 [m]) : 125.3 [kg] (= 903 [gram] per metre)
diameter cable : 12.1 [mm]
weight fin & rudder (7.2 [m2]) : 90.6 [kg]
weight stabilizer & elevator (12.6 [m2]): 156.7 [kg]
total weight wing surfaces & bracing : 2204 [kg] (28.9 [%])
*******************************************************************
wheel pressure : 3810.0 [kg]
weight 2 wheels (1080 [mm] by 216 [mm]) : 161.1 [kg]
weight tailwheel(s) : 5.9 [kg]
weight wheel hydraulic operated retraction system : 29.5 [kg]
weight undercarriage with axle 246.7 [kg]
total weight landing gear : 443.2 [kg] (5.8 [%]
*******************************************************************
********************************************************************
calculated empty weight : 5057 [kg](66.4 [%])
weight oil for 4.0 hours flying : 58.8 [kg]
calculated operational weight empty : 5116 [kg] (67.1 [%])
published operational weight empty : 5085 [kg] (66.7 [%])
weight crew : 243 [kg]
weight fuel for 2.0 hours flying : 441 [kg]
weight catering : 20.0 [kg]
weight water : 8.0 [kg]
********************************************************************
operational weight empty: 5827 [kg](76.5 [%])
weight 15 passengers : 1155 [kg]
weight luggage & freight : 345 [kg]
operational weight loaded: 7327 [kg](96.2 [%])
fuel reserve : 292.6 [kg] enough for 1.33 [hours] flying
operational weight fully loaded : 7620 [kg] with fuel tank filled for 88 [%]
published maximum take-off weight : 7620 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 7.25 [kg/kW]
power loading (operational without useful load) : 5.54 [kg/kW]
power loading (Take-off) 1 PUF: 14.49 [kg/kW]
total power : 1051.4 [kW] at 2000 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 5.8 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.9 [g]
design flight time : 2.66 [hours]
design cycles : 5404 sorties, design hours : 14383 [hours]
operational wing loading : 509 [N/m^2]
wing stress (3 g) during operation : 124 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.74 ["]
max. angle of attack (stalling angle) : 12.25 ["]
angle of attack at max. speed : 0.24 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. angle of attack : 1.28 [ ]
lift coefficient at max. speed : 0.18 [ ]
induced drag coefficient at max. speed : 0.0017 [ ]
drag coefficient at max. speed : 0.0271 [ ]
drag coefficient (zero lift) : 0.0254 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 7400 [kg]): 103 [km/u]
landing speed at sea-level (normal landing weight : 6017 [kg]): 107 [km/hr]
max. endurance speed : 128 [km/u] min. brpu : 113 [kg/hr] at cruise height : 100 [m]
max. rate of climb speed : 159.4 [km/hr] at sea-level
max. range speed : 193 [km/u] min.fuel cons.: 0.707 [kg/km] at cruise height : 4253 [m]
cruising speed : 260 [km/hr] at 3506 [m] (power:71 [%])
maximum speed : 274 [km/hr] at 2400 [m] (power:88 [%])
climbing speed at sea-level (loaded) : 337 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 88 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 125.8 [km/u]
emergency/TO power : 760 [hp] at 2077 [rpm]
static prop wash : 206 [km/u]
take-off distance at sea-level : 184 [m]
lift/drag ratio : 13.91 [ ]
climb to 1000m with max payload : 3.10 [min]
climb to 2000m with max payload : 6.77 [min]
climb to 3000m with max payload : 11.52 [min]
practical ceiling (operational weight 5827 [kg] ) : 7600 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:7510 [kg] ) : 6300 [m]
calculation *10* (action radius & endurance)
published range : 866 [km] with 3 crew and 1528.1 [kg] useful load and 88.1 [%] fuel
range : 899 [km] with 3 crew and 1500.0 [kg] useful load and 91.5 [%] fuel
range : 1129 [km] with 15.0 passengers with each 10 [kg] luggage and 114.9 [%] fuel
Available Seat Kilometres (ASK) : 16942 [paskm]
max range theoretically with additional fuel tanks total 3306.0 [litre] fuel : 3428 [km]
useful load with range 500km : 2000 [kg]
useful load with range 500km : 15 passengers
production (useful load): 521 [tonkm/hour]
production (passengers): 3904 [paskm/hour]
oil and fuel consumption per tonkm : 0.45 [kg]
fuel cost per paskm : 0.045 [eur]
crew cost per paskm : 0.058 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 65 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.056 [eur]
insurance per paskm : 0.044 [eur]
rigging cost per paskm : 0.030 [eur]
maintenance cost per paskm : 0.258 [eur]
direct operating cost per paskm : 0.461 [eur]
direct operating cost per tonkm : 4.607 [eur]
Literature :
Piston-engined airliners page 32,33
Praktisch handboek vliegtuigen deel 2
Curtiss T-32 Condor II - Wikipedia
Fleet - Curtiss Condor (sr692.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 22 October 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4
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