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weight and performance calculations for the Bellanca CH-300 Pacemaker
Bellanca CH-300 Pacemaker
role : medium weight passenger aircraft
importance : ****
first flight : operational : July 1929
country : United States of America
design : Giuseppe Mario Bellanca
production : 35 aircraft
general information :
The Pacemaker was renowned for it long distance flying capabilities. It was reliable
and could carry a heavy load for its size.
users :
crew : 1 passengers : 5
engine : 1 Wright R-975 J-6-9 Whirlwind air-cooled 9 -cylinder radial engine 300 [hp](223.7 KW)
compressor height 1000
dimensions :
wingspan : 14.12 [m], length : 8.5 [m], height : 2.5[m]
wing area : 25.4 [m^2]
weights :
max.take-off weight : 1847 [kg]
empty weight operational : 1032 [kg] useful load : 500 [kg]
performance :
maximum speed :225 [km/hr] at sea-level
cruise speed :202 [km/u] op 100 [m]
service ceiling : 5490 [m]
range : 1086 [km]
description :
parasol wing with fixed landing gear and tail strut
two spar wing
engines, landing gear, fuel and useful load in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed metal Curtiss Reed tractor airscrew with max. efficiency :0.71 [ ]
estimated diameter airscrew 2.64 [m]
angle of attack prop : 16.78 [ ]
reduction : 1.00 [ ]
airscrew revs : 2000 [r.p.m.]
pitch at Max speed 1.87 [m]
blade-tip speed at Vmax and max revs. : 283 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.07 [m]
mean wing chord : 1.80 [m]
calculated wing chord (rounded leading edge tips): 1.90 [m]
wing aspect ratio : 7.85 []
Span : 46 ft 4 in = 14.12m length : 27 ft 9 in = 8.46m height : 8 ft 4 in = 2.54m
seize (span*length*height) : 300 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 4.0 [kg/hr]
fuel consumption(cruise speed) : 48.7 [kg/hr] (66.4 [litre/hr]) at 71 [%] power
distance flown for 1 kg fuel : 4.16 [km/kg] at 2745 [m] height, sfc : 308.5 [kg/kwh]
estimated total fuel capacity : 404 [litre] (296 [kg])
calculation : *3* (weight)
weight engine(s) dry : 306.0 [kg] = 1.37 [kg/KW]
weight 34.5 litre oil tank : 2.93 [kg]
oil tank filled with 1.7 litre oil : 1.5 [kg]
oil in engine 1.2 litre oil : 1.1 [kg]
fuel in engine 1.5 litre fuel : 1.12 [kg]
weight 28.2 litre gravity patrol tank(s) : 4.2 [kg]
weight inertia starter : 5.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 20.8 [kg]
total weight propulsion system : 340 [kg](18.4 [%])
Many Pacemakers had floats and were used as bush plane in Canada and Alaska
***************************************************************
fuselage skeleton (steel tubes) : 4.78 [cm]): 153 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 2.5 rows
weight 5.0 windows : 4.50 [kg]
passenger cabin width : 1.05 [m] cabin length : 2.17 [m] cabin height : 1.80 [m]
weight cabin furbishing : 8.07 [kg]
weight cabin floor : 14.68 [kg]
bracing : 9.2 [kg]
fuselage covering ( 13.6 [m2] doped linen fabric) : 4.1 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 5.1 [kg]
weight seats : 30.0 [kg]
weight 376 [litre] main fuel tank empty : 30.1 [kg]
weight air conditioning : 8 [kg]
weight engine mounts & firewalls : 11 [kg]
total weight fuselage : 281 [kg](15.2 [%])
***************************************************************
weight plywood wing covering : 30 [kg]
total weight ribs (56 ribs) : 110 [kg]
load on front upper spar (clmax) per running metre : 1006.7 [N]
load on rear upper spar (vmax) per running metre : 385.9 [N]
total weight 4 spars : 115 [kg]
weight wings : 255 [kg]
weight wing/square meter : 10.03 [kg]
cantilever wing without bracing cables
weight fin & rudder (2.3 [m2]) : 23.6 [kg]
weight stabilizer & elevator (2.9 [m2]): 28.8 [kg]
total weight wing surfaces & bracing : 307 [kg] (16.6 [%])
*******************************************************************
wheel pressure : 923.5 [kg]
weight 2 wheels (890 [mm] by 137 [mm]) : 38.4 [kg]
weight tailskid : 4.1 [kg]
weight undercarriage with axle 49.1 [kg]
total weight landing gear : 91.7 [kg] (5.0 [%]
*******************************************************************
********************************************************************
calculated empty weight : 1020 [kg](55.2 [%])
weight oil for 6.4 hours flying : 25.9 [kg]
calculated operational weight empty : 1046 [kg] (56.6 [%])
published operational weight empty : 1032 [kg] (55.9 [%])
***o***
"
weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 97 [kg]
********************************************************************
operational weight empty: 1224 [kg](66.3 [%])
weight 5 passengers : 385 [kg]
weight luggage & freight : 115 [kg]
operational weight loaded: 1724 [kg](66.3 [%])
fuel reserve : 122.8 [kg] enough for 2.52 [hours] flying
operational weight fully loaded : 1847 [kg] with fuel tank filled for 74 [%]
published maximum take-off weight : 1847 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 8.26 [kg/kW]
power loading (operational without useful load) : 5.47 [kg/kW]
total power : 223.7 [kW] at 2000 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.4 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.0 [g]
design flight time : 3.75 [hours]
design cycles : 3846 sorties, design hours : 14438 [hours]
operational wing loading : 473 [N/m^2]
wing stress (3 g) during operation : 141 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.17 ["]
max. angle of attack (stalling angle) : 12.29 ["]
angle of attack at max. speed : 1.17 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max. speed : 0.20 [ ]
induced drag coefficient at max. speed : 0.0022 [ ]
drag coefficient at max. speed : 0.0422 [ ]
drag coefficient (zero lift) : 0.0400 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 1798 [kg]): 113 [km/u]
landing speed at sea-level: 133 [km/hr]
min. drag speed (max endurance) : 150 [km/hr] at 2745 [m](power :43 [%])
min. power speed (max range) : 150 [km/hr] at 2745 [m] (power:43 [%])
max. rate of climb speed : 130.7 [km/hr] at sea-level
cruising speed : 202 [km/hr] op 2745 [m] (power:69 [%])
design speed prop : 214 [km/hr]
maximum speed : 225 [km/hr] op 100 [m] (power:106 [%])
climbing speed at sea-level : 457 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 137.6 [km/u]
static prop wash : 149 [km/u]
take-off distance at sea-level : 256 [m]
lift/drag ratio : 10.75 [ ]
climb to 1000m with max payload : 4.04 [min]
climb to 2000m with max payload : 8.99 [min]
climb to 3000m with max payload : 15.23 [min]
practical ceiling (operational weight 1224 [kg] ) : 7493 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:1823 [kg] ) : 5393 [m]
max. dive speed : 491.4 [km/hr] at 4393 [m] height
turning speed at CLmax : 159.2 [km/u] at 50 [m] height
turn radius at 50m: 73 [m]
time needed for 360* turn 10.4 [seconds] at 50m
load factor at max. angle turn 2.89 ["g"]
calculation *10* (action radius & endurance)
published range : 1086 [km] with 1 crew and 459.2 [kg] useful load and 88.1 [%] fuel
range : 916 [km] with 1 crew and 500.0 [kg] useful load and 74.3 [%] fuel
range : 1187 [km] with 5.0 passengers with each 10 [kg] luggage and 96.3 [%] fuel
Available Seat Kilometers (ASK) : 5933 [paskm]
max range theoretically with additional fuel tanks total 982.4 [litre] fuel : 2997.2 [km]
useful load with range 500km : 600 [kg]
useful load with range 500km : 5 passengers
production (useful load): 121.50 [tonkm/hour]
production (passengers): 1012.50 [paskm/hour]
oil and fuel consumption per tonkm : 0.43 [kg]
oil and fuel consumption per paskm : 0.05 [kg]
fuel cost per paskm : 0.05 [eur]
crew cost per paskm : 0.15 [eur]
_
°
economic hours : 12775 [hours] is less then design hours
time between engine failure : 235 [hr]
writing off per paskm : 0.06 [eur]
insurance per paskm : 0.0356 [eur]
maintenance cost per paskm : 0.1820 [eur]
direct operating cost per paskm : 0.48 [eur]
Literature :
Piston-engined airliners
Wikipedia
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/
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(c) B van der Zalm 10 May 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4