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weight and performance calculations for the Airco D.H.9C
Airco D.H.9C
role : air taxi
importance : ****
first flight : late 1921 operational : January 1922
country : United-Kingdom
design : Geoffrey de Havilland
production : 19 aircraft
general information :
Converted DH9 light bomber
users :
registrations : G-EBOD, G-EBAX, G-EAYT
crew : 1 passengers : 3
engine : 1 Armstrong Siddeley Puma liquid-cooled 6 -cylinder inline engine 230 [hp](171.5 KW)
dimensions :
wingspan : 12.92 [m], length : 9.29 [m], height : 3.4[m]
wing area : 40.3 [m^2]
weights :
max.take-off weight : 1675 [kg]
empty weight operational (estimation): 1075.0 [kg] useful load : 300 [kg]
performance :
maximum speed :185 [km/u] op 500 [m]
cruise speed :166 [km/u] op 500 [m]
service ceiling : 4000 [m]
range : 805 [km]
description :
2-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
engines, landing gear, fuel and useful load in or attached to the fuselage
airscrew :
fixed pitch 4 -bladed tractor airscrew with max. efficiency :0.59 [ ]
diameter airscrew 2.90 [m]
angle of attack prop : 21.15 [ ]
reduction : 1.00 [ ]
airscrew revs : 1400 [r.p.m.]
pitch at Max speed 2.20 [m]
blade-tip speed at Vmax and max revs. : 184 [m/s]
calculation : *1* (dimensions)
wing chord : 1.67 [m]
mean wing chord : 1.56 [m]
calculated wing chord (rounded tips): 1.71 [m]
wing aspect ratio : 8.28 []
gap : 1.67 [m]
gap/chord : 1.07 [ ]
seize (span*length*height) : 408 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.4 [kg/hr]
fuel consumption(cruise speed) : 37.9 [kg/hr] (51.7 [litre/hr]) at 65 [%] power
distance flown for 1 kg fuel : 4.39 [km/kg] at 2000 [m] cruise height, sfc : 342.0 [kg/kwh]
estimated total fuel capacity : 283.84 [litre] (208.06 [kg])
calculation : *3* (weight)
weight engine(s) dry : 308.0 [kg] = 1.80 [kg/KW]
weight 26.5 litre oil tank : 2.25 [kg]
oil tank filled with 1.3 litre oil : 1.2 [kg]
oil in engine 9.6 litre oil : 8.6 [kg]
fuel in engine 1.2 litre fuel : 0.86 [kg]
weight 22.0 litre gravity patrol tank(s) : 3.3 [kg]
weight radiator : 27.4 [kg]
weight exhaust pipes & fuel lines 21.0 [kg]
weight self-starter : 4.2 [kg]
weight cowling 6.9 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 87.5 [kg]
total weight propulsion system : 469 [kg](28.0 [%])
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fuselage skeleton (wood gauge : 7.14 [cm]): 121 [kg]
cabin layout : pitch : 87 [cm] (1+0) seating in 3.0 rows
weight 6.0 windows : 5.40 [kg]
passenger cabin width : 0.74 [m] cabin length : 2.61 [m] cabin height : 1.40 [m]
weight cabin furbishing : 5.24 [kg]
weight cabin floor : 12.31 [kg]
bracing : 7.9 [kg]
fuselage covering ( 16.3 [m2] doped linen fabric) : 4.9 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 5.2 [kg]
weight seats : 20.0 [kg]
weight 262 [litre] main fuel tank empty : 20.9 [kg]
weight air conditioning : 4 [kg]
weight engine mounts & firewalls : 9 [kg]
total weight fuselage : 220 [kg](13.1 [%])
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weight wing covering (doped linen fabric) : 34 [kg]
total weight ribs (88 ribs) : 100 [kg]
load on front upper spar (clmax) per running metre : 778.6 [N]
load on rear upper spar (vmax) per running metre : 373.2 [N]
total weight 8 spars : 74 [kg]
weight wings : 208 [kg]
weight wing/square meter : 5.15 [kg]
weight 8 interplane struts & cabane : 23.2 [kg]
weight cables (74 [m]) : 8.7 [kg] (= 117 [gram] per metre)
diameter cable : 4.4 [mm]
weight fin & rudder (1.9 [m2]) : 10.3 [kg]
weight stabilizer & elevator (4.5 [m2]): 23.7 [kg]
total weight wing surfaces & bracing : 274 [kg] (16.3 [%])
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wheel pressure : 837.5 [kg]
weight 2 wheels (810 [mm] by 125 [mm]) : 31.6 [kg]
weight tailskid : 5.5 [kg]
weight undercarriage with axle 45.7 [kg]
total weight landing gear : 82.8 [kg] (4.9 [%]
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calculated empty weight : 1045 [kg](62.4 [%])
weight oil for 5.8 hours flying : 19.9 [kg]
weight cooling fluids : 37.0 [kg]
calculated operational weight empty : 1102 [kg] (65.8 [%])
estimated operational weight empty : 1075 [kg] (64.2 [%])
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weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 76 [kg]
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operational weight empty: 1259 [kg](75.2 [%])
weight 3 passengers : 231 [kg]
weight luggage & freight : 69 [kg]
operational weight loaded: 1559 [kg](75.2 [%])
fuel reserve : 116.1 [kg] enough for 3.06 [hours] flying
operational weight fully loaded : 1675 [kg] with fuel tank filled for 92 [%]
published maximum take-off weight : 1675 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 9.77 [kg/kW]
power loading (operational without useful load) : 7.34 [kg/kW]
total power : 171.5 [kW] at 1400 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.5 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 3.38 [hours]
design cycles : 1005 sorties, design hours : 3400 [hours]
operational wing loading : 306 [N/m^2]
wing stress (3 g) during operation : 178 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.39 ["]
max. angle of attack (stalling angle) : 11.88 ["]
angle of attack at max. speed : 0.91 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.12 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max. speed : 0.20 [ ]
induced drag coefficient at max. speed : 0.0027 [ ]
drag coefficient at max. speed : 0.0292 [ ]
drag coefficient (zero lift) : 0.0265 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 75 [km/u]
stalling speed at sea-level (MTOW): 87 [km/u]
landing speed at sea-level: 88 [km/hr]
min. drag speed (max endurance) : 113 [km/hr] at 2000 [m](power :37 [%])
min. power speed (max range) : 120 [km/hr] at 2000 [m] (power:39 [%])
max. rate of climb speed : 112.5 [km/hr] at sea-level
cruising speed : 166 [km/hr] op 2000 [m] (power:64 [%])
design speed prop : 176 [km/hr]
maximum speed : 185 [km/hr] op 500 [m] (power:93 [%])
climbing speed at sea-level : 264 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 104.1 [km/u]
static prop wash : 114 [km/u]
take-off distance at sea-level : 178 [m]
lift/drag ratio : 11.76 [ ]
climb to 1000m with max payload : 7.85 [min]
climb to 2000m with max payload : 20.85 [min]
climb to 3000m with max payload : 43.06 [min]
published ceiling (4000 [m]
practical ceiling (operational weight) : 4728 [m] with flying weight :1259 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 3433 [m] with flying weight :1656 [kg]
max. dive speed : 368.3 [km/hr] at 2433 [m] height
turning speed at CLmax : 112.7 [km/u] at 50 [m] height
turn radius at 50m: 50 [m]
time needed for 360* turn 10.0 [seconds] at 50m
load factor at max. angle turn 2.23 ["g"]
calculation *10* (action radius & endurance)
published range : 805 [km] with 1 crew and 308.6 [kg] useful load and 88.1 [%] fuel
range : 843 [km] with 1 crew and 300.0 [kg] useful load and 92.3 [%] fuel
max range theoretically with additional fuel tanks for total 671.1 [litre] fuel : 2160.4 [km]
useful load with range 500km : 378 [kg]
production : 62.95 [tonkm/hour]
oil and fuel consumption per tonkm : 0.66 [kg]
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Fatal accidents :
02 October 1922 D.H.9C G-EAYT crashed shortly after take-off from Venice apt. in the sea. All 3 passengers and 1 pilot killed. Destination : London.
Literature :
Piston-engined airliners page 8
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 05 February 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4