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weight and performance calculations for the De Havilland D.H.104 Dove srs.1
De Havilland D.H.104 Dove srs.1
role : light passenger aircraft
importance : ****
first flight : 25 September 1945 operational : December 1946
country : United-Kingdom
design : Ronald Bishop
production : 544 aircraft including 127 military variants (RAF Devon) between 1946 and
1967, first at Hatfield but from 1951 at Broughton, near Chester.
general information :
Successful short-haul airliner. Monoplane successor of the pre-war Dragon Rapide.
Max. Landing weight : 3856 kg fuel capacity : 168 imp. gallon (764 litres), optional 52 imp. gallon (236 litres) tank in rear luggage compartment. Oil capacity : 7 imp. gallon (31.8 litres)
The extensive use of special Redux metal-bonding adhesives reduced the need for riveting during the manufacturing process, reducing overall weight and air-skin friction .
A TKS anti-icing system was available for the Dove, involving an alcohol -based jelly delivered via porous metal strips embedded on the leading edges of the wings and tail.
In the United States the Dove was popular as executive aircraft.
primary users : Central African Airways, Lan Chile(12), Argentine air force (70), LTU,
Martin’s Air Charter, Channel Airways, Philips and many more.
flight crew : 2 cabin crew : 0 passengers : 8 - 11
powerplant : 2 De Havilland Gipsy Queen 70-3 air-cooled 6 -cylinder inverted inline piston engine 285 [hp](212.5 KW)
normal rating, supercharged engine, low blower, constant power to height : 2135 [m]
and with 330 [hp](246.1 KW) available for take-off
dimensions :
wingspan : 17.37 [m], length : 11.99 [m], height : 3.96 [m]
wing area : 31.1 [m^2]
weights :
max.take-off weight : 3855 [kg]
empty weight operational : 2484 [kg] useful load : 950 [kg]
performance :
maximum continuous speed : 357 [km/u] op 2135 [m]
normal cruise speed : 322 [km/u] op 2590 [m] (74 [%] power)
service ceiling : 6600 [m]
range with max fuel : 1650 [km] and allowance for 61.8 [km] diversion and 30 [min]
hold
description :
low-winged monoplane with retractable landing gear with nose wheel
tapered wing with Fowler flaps airfoil : root RAF 34 mod (18.3%) tip RAF 34
mod (14.5%)
engines and landing gear attached to the wings, fueltanks in the wings
construction : all-metal stressed-skin (Alclad-aluminium) airplane
fuselage shape : []
airscrew :
two Hawker Siddeley Hydromatic constant speed feathering 3 -bladed tractor
airscrews with max. efficiency :0.77 [ ]
diameter airscrew 2.29 [m]
relative pitch (J) : 1.41 [ ]
power loading prop : 61.87 [KW/m]
theoretical pitch without slip : 3.61 [m]
blade angle prop at max.speed : 34.82 [ ]
reduction : 0.71 [ ]
airscrew revs : 1849 [r.p.m.]
aerodynamic pitch at max. continuous speed 3.22 [m]
blade-tip speed at max.continuous speed : 243 [m/s]
propellor noise in flight : 85 [Db]
calculation : *1* (dimensions)
measured wing chord : 1.72 [m] at 50% wingspan
mean wing chord : 1.79 [m]
calculated average wing chord tapered wing with rounded tips: 1.73 [m]
wing aspect ratio : 9.7 []
seize (span*length*height) : 825 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.0 [kg/hr]
fuel consumption (econ. cruise speed) : 96.4 [kg/hr] (131.5 [litre/hr]) at 74 [%] power
distance flown for 1 kg fuel : 3.34 [km/kg] at 2590 [m] height, sfc : 307.0 [kg/kwh]
estimated total fuel capacity : 765 [litre] (561 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 600.0 [kg] = 1.41 [kg/KW]
weight 51.4 litre oil tank : 4.37 [kg]
oil tank filled with 3.2 litre oil : 2.9 [kg]
oil in engine 2.4 litre oil : 2.1 [kg]
fuel in engine 2.9 litre fuel : 2.13 [kg]
weight 55.9 litre gravity patrol tank(s) : 8.4 [kg]
weight Burgess type silencers : 8.5 [kg]
weight Rotax starter : 5.2 [kg]
weight cowling 8.5 [kg]
weight variable pitch control : 1.6 [kg]
weight airscrew(s) incl. boss & bolts : 39.7 [kg]
total weight propulsion system : 682 [kg](17.7 [%])
***************************************************************
fuselage aluminium frame : 315 [kg]
cabin layout : pitch : 81 [cm] (1+1) seating in 4 rows
pax density (normal seating) : 0.84 [m2/pax]
high density seating without toilet, only for short hops
high density seating passengers : 11 at 2 -abreast seating in 5.5 rows
weight 1 toilets : 8.0 [kg]
weight 2 hand fire extinguisher : 6 [kg]
weight 10 windows : 9.0 [kg]
weight 1 entrance/exit doors : 5.0 [kg]
extra main deck space for freight/mail/luggage etc. : 0.35 [m3]
cabin volume (usable), excluding flight deck : 8.55 [m3]
passenger cabin max.width : 1.37 [m] cabin length : 4.89 [m] cabin height : 1.60 [m]
fuselage covering ( 43.5 [m2] duraluminium 1.79 [mm]) : 202.0 [kg]
weight floor beams : 1.5 [kg]
weight cabin furbishing : 18.1 [kg]
weight cabin floor : 25.9 [kg]
fuselage (sound proof) isolation : 8.9 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight instruments. : 6.0 [kg]
weight lighting : 2.0 [kg]
weight electricity generator : 2.0 [kg]
weight dual controls + indicators: 20.0 [kg]
weight seats : 50.0 [kg]
no cabin heating, only fresh air ventilation
weight air conditioning : 2 [kg]
total weight fuselage : 677 [kg](17.6 [%])
***************************************************************
total weight aluminium ribs (110 ribs) : 137 [kg]
weight engine mounts : 21 [kg]
weight two 355 [litre] main fuel tanks empty : 56.7 [kg]
weight wing covering (painted aluminium 1.66 [mm]) : 279 [kg]
total weight aluminium spars (multi-cellular wing structure) : 165 [kg]
Dove operated by East Indonesian airline SAATAS pictured at Darwin apt. in the 1980’s. Note the lowered flap.
weight wings : 582 [kg]
weight wing/square meter : 18.72 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 19.1 [kg]
weight fin & rudder (3.5 [m2]) : 66.1 [kg]
weight stabilizer & elevator (3.5 [m2]): 65.7 [kg]
weight fowler flaps (2.6 [m2]) : 30.3 [kg]
total weight wing surfaces & bracing : 841 [kg] (21.8 [%])
*******************************************************************
wheel pressure : 1927.5 [kg]
weight 2 Dunlop main wheels (710 [mm] by 118 [mm]) : 75.0 [kg]
weight nose wheel : 9.4 [kg]
weight pneumatic wheel-brakes : 3.4 [kg]
weight Dowty shock absorbers : 4.6 [kg]
weight wheel pneumatic operated retraction system : 20.7 [kg]
weight undercarriage struts with axle 125.1 [kg]
total weight landing gear : 248.8 [kg] (6.5 [%]
*******************************************************************
The Dove was capable to accommodate 11 passengers, the toilet in the back had to be removed for this and for 2 additional seats in the tail cone the rear luggage compartment had to be omitted.
********************************************************************
calculated empty weight : 2449 [kg](63.5 [%])
weight oil for 6.1 hours flying : 36.6 [kg]
calculated operational weight empty : 2485 [kg] (64.5 [%])
published operational weight empty : 2484 [kg] (64.4 [%])
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 193 [kg]
********************************************************************
operational weight empty: 2840 [kg](73.7 [%])
weight 8 passengers : 616 [kg]
weight luggage : 98 [kg]
weight cargo : 236 [kg]
operational weight loaded: 3790 [kg](98.3 [%])
fuel reserve : 64.7 [kg] enough for 0.67 [hours] flying
operational weight fully loaded : 3855 [kg] with fuel tank filled for 46 [%]
published maximum take-off weight : 3855 [kg] (100.0 [%])
Interior of German LTU Dove
calculation : * 4 * (engine power)
power loading (Take-off) : 7.83 [kg/kW]
power loading (operational without useful load) : 6.68 [kg/kW]
power loading (Take-off) 1 PUF: 15.67 [kg/kW]
max.total take-off power : 492.2 [kW]
calculation : *5* (loads)
manoeuvre load : 3.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.5 [g]
design flight time : 3.59 [hours]
design cycles : 12591 sorties, design hours : 45164 [hours]
operational wing loading : 1190 [N/m^2]
wing stress (3 g) during operation : 191 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.33 ["]
max. angle of attack (stalling angle, clean) : 11.15 ["]
max. angle of attack (full flaps) : 10.26 ["]
angle of attack at max. speed : 0.71 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.12 [ ]
lift coefficient at max. speed : 0.18 [ ]
lift coefficient at max. angle of attack : 1.12 [ ]
max.lift coefficient full flaps : 1.55 [ ]
induced drag coefficient at max.speed : 0.0014 [ ]
drag coefficient at max. speed : 0.0208 [ ]
drag coefficient (zero lift) : 0.0194 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 3759 [kg]): 149 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 117 [km/u]
landing speed at sea-level (normal landing weight : 3694 [kg]): 135 [km/hr]
Close-up of German D-INKA
max. rate of climb speed : 153 [km/hr] at sea-level
max. endurance speed : 154 [km/u] min.fuel/hr : 38 [kg/hr] at height : 610 [m]
max. range speed : 229 [km/u] min. fuel consumption : 0.224 [kg/km] at cruise height :
3962 [m]
cruising speed : 322 [km/hr] at 2590 [m] (power:75 [%])
max. continuous speed* : 357.00 [km/hr] at 2135 [m] (power:100 [%])
climbing speed at sea-level (loaded) : 363 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 111 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 181.6 [km/u]
emergency/TO power : 330 [hp] at 2800 [rpm]
static prop wash : 151 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 423 [m]
take-off distance at sea-level over 15 [m] height : 529 [m]
landing run : 363 [m]
landing run from 15 [m] : 599 [m]
lift/drag ratio : 17.44 [ ]
climb to 1000m with max payload : 2.89 [min]
climb to 2000m with max payload : 5.86 [min]
climb to 3000m with max payload : 9.57 [min]
climb to 5000 [m] with max payload : 25.27 [min]
practical ceiling (operational weight empty 2840 [kg] ) : 8200 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:3807 [kg] ) : 6600 [m]
calculation *10* (action radius & endurance)
published range : 1650 [km] with 2 crew and 713.6 [kg] useful load and 88.1 [%] fuel (no reserves)
range : 860 [km] with 2 crew and 950.0 [kg] useful load and 45.9 [%] fuel
range : 1650 [km] with 8.0 passengers with each 12.2 [kg] luggage and 88.1 [%] fuel
Available Seat Kilometres (ASK) : 13200 [paskm]
max range theoretically with additional fuel tanks total 1757.8 [litre] fuel : 5763 [km]
useful load with range 500km : 1139 [kg]
useful load with range 500km : 8 passengers
production (theor.max load): 367 [tonkm/hour]
production (useful load): 306 [tonkm/hour]
production (passengers): 2576 [paskm/hour]
oil and fuel consumption per tonkm : 0.279 [kg]
fuel cost per paskm : 0.040 [eur]
crew cost per paskm : 0.058 [eur]
economic hours : 18250 [hours] is less then design hours
time between engine failure : 8102 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.043 [eur]
insurance per paskm : 0.0003 [eur]
maintenance cost per paskm : 0.104 [eur]
direct operating cost per paskm : 0.245 [eur]
direct operating cost per tonkm (max. load): 1.724 [eur]
direct operating cost per tonkm (normal useful load): 2.067 [eur]
Literature :
Praktisch handboek vliegtuigen deel 5 page 108,109
Piston-engined airliners page 61,62
Jane’s fighting aircraft WWII page 113,114
Jane’s pocket book 5 Military transport & training aircraft page 77
Verkeersvliegtuigen nu en straks page 26,27
Onze burgervloot page 22
* max. continuous speed : max. level speed maintainable for minimal 30 min.
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
SABRENA OO-CFE in Congo, 1953
South African Dove. The air-cooled engine was easy to access for maintenance.
(c) B van der Zalm 03 April 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4