Aircraft investigation info>>>>>>> HOME PAGE
weight and performance calculations for the Airco (De Havilland) D.H.16
Airco (De Havilland) D.H.16
role : light passenger aircraft
importance : ***
first flight : March 1919 Hendon Aerodrome operational : August 1919
country : United-Kingdom
design : Geoffrey de Havilland
production : 9 aircraft
general information :
The D.H.16 was a redesigned D.H.9A with a wider fuselage to give room for four passengers in an enclosed cabin behind the pilot. The passengers sat cross facing each other in pairs, the cabin was too small to sit beside each other.
8 aircraft were delivered to AT&T (Aircraft Transport & Travel) who started a scheduled service from London (Hounslow) to Paris on 25 August 1919.
1 aircraft was sold to Argentina and was flying between Buenos Aires and Montevideo.
On 17 May 1920 a D.H.16 G-EALU flew the first KLM service between Amsterdam and London (Croydon).
Already in December 1920 AT&T closed down and the seven remaining aircraft were stored. Two were later used for newspaper delivery flights, the other 5 being scrapped.
After a fatal crash in 1923 the remaining D.H.16 were taken out of service
users : AT&T, River Plate Aviation (Argentina)
Registrations : G-EALU, G-EALM, K-130, G-EAQS
crew : 1 passengers : 4
engine : 1 Rolls Royce Eagle VIII liquid-cooled 12 -cylinder V-engine 345 [hp](257.3 KW)
dimensions :
wingspan : 14.15 [m], length : 9.72 [m], height : 3.45[m]
wing area : 45.5 [m^2]
weights :
max.take-off weight : 2130 [kg]
empty weight operational : 1380 [kg] useful load : 400 [kg]
performance :
maximum speed :200 [km/u] op 500 [m]
cruise speed :180 [km/u] op 500 [m]
service ceiling : 4000 [m]
range : 684 [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 :0.58 [ ]
estimated diameter airscrew 2.87 [m]
angle of attack prop : 30.86 [ ]
coarse pitch
reduction : 0.60 [ ]
airscrew revs : 990 [r.p.m.]
pitch at Max speed 3.37 [m]
blade-tip speed at Vmax and max revs. : 136 [m/s]
calculation : *1* (dimensions)
wing chord : 1.75 [m]
mean wing chord : 1.61 [m]
calculated wing chord (rounded tips): 1.76 [m]
wing aspect ratio : 8.80 []
gap : 1.68 [m]
gap/chord : 1.04 [ ]
seize (span*length*height) : 475 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.9 [kg/hr]
fuel consumption(cruise speed) : 57.3 [kg/hr] (78.1 [litre/hr]) at 63 [%] power
distance flown for 1 kg fuel : 3.14 [km/kg] at 2000 [m] cruise height, sfc : 355.0 [kg/kwh]
estimated total fuel capacity : 337.00 [litre] (247.02 [kg])
calculation : *3* (weight)
weight engine(s) dry : 380.8 [kg] = 1.48 [kg/KW]
weight reduction gear : 28.3 [kg]
weight 26.0 litre oil tank : 2.21 [kg]
oil tank filled with 1.9 litre oil : 1.7 [kg]
oil in engine 14.3 litre oil : 12.9 [kg]
fuel in engine 1.8 litre fuel : 1.29 [kg]
weight 33.2 litre gravity patrol tank(s) : 5.0 [kg]
Length : 31 ft 10.5 in = 9.72m span 46ft 5.125in = 14.15m gap 5 ft 6 in = 1.68m total area main planes : 436.5 sq ft = 40.55m2 chord 5 ft 9 in = 1.75m
weight radiator : 41.2 [kg]
weight exhaust pipes & fuel lines 30.4 [kg]
weight self-starter : 6.3 [kg]
weight cowling 10.3 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 87.3 [kg]
total weight propulsion system : 634 [kg](29.7 [%])
***************************************************************
fuselage skeleton (wood gauge : 8.04 [cm]): 161 [kg]
fuselage width : 0.95 [m]
cabin layout : pitch : 58 [cm] (1+0) seating in 4.0 rows
passenger cabin area : 1.83 [m2]
weight 8.0 windows : 7.20 [kg]
passenger cabin width : 0.79 [m] cabin length : 2.32 [m] cabin height : 1.40 [m]
cabin space : 2.56 [m3]
weight cabin furbishing : 9.57 [kg]
DH16 with 450 hp Napier Lion W-engine
The first six aircraft were powered by a 320 hp (239 kW) Rolls Royce Eagle inline piston engine ; the last three aircraft were fitted with the more powerful 450 hp (336 kW) Napier Lion engine. Max speed with the Lion engine was 219 km/hr.
bracing : 11.0 [kg]
fuselage covering ( 17.8 [m2] doped linen fabric) : 5.3 [kg]
weight instruments. : 2.5 [kg]
weight lighting : 1.1 [kg]
weight controls : 5.5 [kg]
weight seats : 15.0 [kg]
weight 304 [litre] main fuel tank empty : 24.3 [kg]
weight air conditioning : 6 [kg]
weight engine mounts & firewalls : 13 [kg]
total weight fuselage : 261 [kg](12.3 [%])
***************************************************************
weight wing covering (doped linen fabric) : 37 [kg]
total weight ribs (108 ribs) : 127 [kg]
load on front upper spar (clmax) per running metre : 903.4 [N]
load on rear upper spar (vmax) per running metre : 434.6 [N]
total weight 8 spars : 104 [kg]
weight wings : 267 [kg]
weight wing/square meter : 5.87 [kg]
weight 8 interplane struts & cabane : 26.6 [kg]
weight cables (79 [m]) : 12.9 [kg] (= 163 [gram] per metre)
diameter cable : 5.2 [mm]
weight fin & rudder (2.3 [m2]) : 14.0 [kg]
weight stabilizer & elevator (5.1 [m2]): 30.4 [kg]
total weight wing surfaces & bracing : 351 [kg] (16.5 [%])
*******************************************************************
Can only operate from paved runways
wheel pressure : 1065.0 [kg]
weight 2 wheels (790 [mm] by 99 [mm]) : 31.8 [kg]
weight tailskid : 7.0 [kg]
weight undercarriage with axle 67.8 [kg]
total weight landing gear : 106.6 [kg] (5.0 [%]
*******************************************************************
********************************************************************
calculated empty weight : 1352 [kg](63.5 [%])
weight oil for 4.6 hours flying : 17.6 [kg]
weight cooling fluids : 55.6 [kg]
calculated operational weight empty : 1425 [kg] (66.9 [%])
published operational weight empty : 1380 [kg] (64.8 [%])
_____________
| | o | |
-------------
"
weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 115 [kg]
********************************************************************
operational weight empty: 1621 [kg](76.1 [%])
weight 4 passengers : 308 [kg]
weight luggage & freight : 92 [kg]
operational weight loaded: 2021 [kg](76.1 [%])
fuel reserve : 109.0 [kg] enough for 1.90 [hours] flying
operational weight fully loaded : 2130 [kg] with fuel tank filled for 90 [%]
published maximum take-off weight : 2130 [kg] (100.0 [%])
||
||
I||==|
||
||
calculation : * 4 * (engine power)
power loading (Take-off) : 8.28 [kg/kW]
power loading (operational without useful load) : 6.30 [kg/kW]
total power : 257.3 [kW] at 1650 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.6 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 3.04 [hours]
design cycles : 263 sorties, design hours : 800 [hours]
operational wing loading : 349 [N/m^2]
wing stress (3 g) during operation : 179 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.37 ["]
max. angle of attack (stalling angle) : 11.67 ["]
angle of attack at max. speed : 0.84 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.12 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
lift coefficient at max. speed : 0.19 [ ]
induced drag coefficient at max. speed : 0.0024 [ ]
drag coefficient at max. speed : 0.0300 [ ]
drag coefficient (zero lift) : 0.0276 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 80 [km/u]
stalling speed at sea-level (MTOW): 92 [km/u]
landing speed at sea-level: 95 [km/hr]
min. drag speed (max endurance) : 117 [km/hr] at 2000 [m](power :34 [%])
min. power speed (max range) : 126 [km/hr] at 2000 [m] (power:36 [%])
max. rate of climb speed : 120.5 [km/hr] at sea-level
cruising speed : 180 [km/hr] op 2000 [m] (power:63 [%])
design speed prop : 190 [km/hr]
maximum speed : 200 [km/hr] op 500 [m] (power:92 [%])
climbing speed at sea-level : 312 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 110.7 [km/u]
propellor partly stalled > high aaprop
static prop wash : 49 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level : 412 [m]
lift/drag ratio : 11.87 [ ]
climb to 1000m with max payload : 6.23 [min]
climb to 2000m with max payload : 16.32 [min]
climb to 3000m with max payload : 32.89 [min]
published ceiling (4000 [m]
practical ceiling (operational weight) : 4623 [m] with flying weight :1621 [kg]
practical ceiling fully loaded (mtow-30 min.fuel) : 3578 [m] with flying weight :2101 [kg]
max. dive speed : 446.0 [km/hr] at 2578 [m] height
turning speed at CLmax : 125.6 [km/u] at 50 [m] height
turn radius at 50m: 56 [m]
time needed for 360* turn 10.1 [seconds] at 50m
load factor at max. angle turn 2.42 ["g"]
calculation *10* (action radius & endurance)
published range : 684 [km] with 1 crew and 405.9 [kg] useful load and 88.1 [%] fuel
range : 702 [km] with 1 crew and 400.0 [kg] useful load and 90.5 [%] fuel
max range theoretically with additional fuel tanks for total 850.6 [litre] fuel : 1959.6 [km]
useful load with range 500km : 464 [kg]
production : 83.60 [tonkm/hour]
oil and fuel consumption per tonkm : 0.73 [kg]
_
I_°==/
°
Fatal crashes :
10 January 1923– De Havilland Aeroplane Hire Service Airco DH.16 G-EALM crashed at Stanmore, Middlesex. The pilot and a passenger were killed, three others were injured.
Literature :
Piston engined airliners page 8
List of accidents and incidents involving airliners in the United Kingdom - 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/
content please mail to below mail address
(c) B van der Zalm 01 January 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4