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weight and performance calculations for the Voisin-Delagrange II
Voisin-Delagrange II
role : experimental/research/flying trials
importance : *****
first flight : 20 January 1908 operational : January 1908
country : France
design : Gabriel (1880-1973) and Charles Voisin (1882-1912)
production : 1 prototype at Billancourt
general information :
The 2nd aircraft the Voisin brothers built was for Leon Delagrange (1872-1910), a
French sculptor.
The first attempt to fly the aircraft was made by Gabriel Voisin on 28 February 1907
at the Polygon de Vincennes, in Paris but the lower booms supporting the tail failed
when he attempted to lift off.
On 30 March 1907 Charles Voisin made a flight of 60m. The aircraft did not have
ailerons or wing warping for lateral control.
On 2 November 1907 Leon Delagrange makes the first flight with this Voisin-
Delagrange I. He makes a flight of 100m, but it was not satisfactory. On 3 November
1907 a flight of 500m was made at Issy. However on 6 November after making another
flight the aircraft was destroyed in a crash-landing. Delagrange ordered directly a new
aircraft. Shortly after Leon Delagrange receives the Voisin- Delagrange II, almost
similar in seize, but incorporating the improvements which Henry Farman had
introduced on his Voisin-Farman biplane. It had a 50 hp Antoinette engine and a
reduced tail span. On 20 January 1908 Delagrange made a flight of 100m.
At 20 March 1908 Delagrange flew a circle of 700m, he was in close competition with
Henry Farman. On 10 April 1908 a flight of 2.5 km was made and the next day
3.9 km. Then Leon Delagrange went to Italy for to give demonstration flights. On 30
May he made a flight of 12.75 km lasting 15 minutes 25 seconds at Rome. (Average
ground speed 49.6 km/u). He only had to came down because the fuel was running
out.
On 23 June 1908 Delagrange made a flight of 14 km in Milano, Italy.
08 July 1908 Turin, Leon Delagrange takes his girlfriend Mme. Therese Peltier (1873-
1926) in the air, the first woman passenger. They make a 200m flight.
On 17 September 1909 Delagrange set a new record by flying 24.125 km in 29 minutes
53 sec. (= av. 48.4 km/u)
Léon Delagrange, was killed 4 January 1910 when the wing of his Blériot XI failed
near Croix d’Hins, near Bordeaux.
users : Leon Delagrange
crew : 1 passengers : 1
engine : 1 Antoinette 50hp liquid-cooled 8 -cylinder V-engine 50 [hp](37.3 KW)
dimensions :
wingspan : 10.0 [m], length : 10.5 [m], height : 3.35[m]
wing area : 42.0 [m^2]
weights :
max.take-off weight : 565 [kg]
empty weight operational : 400 [kg] useful load : 65 [kg]
performance :
maximum speed :62 [km/hr] at sea-level
cruise speed :56 [km/u] op 25 [m]
service ceiling : 25 [m]
endurance : 0.5 [hours]
range : 24 [km]
estimated endurance : 0.50 [hours]
description :
2-bay biplane with fixed landing gear with tail wheel(s)
two spar upper and lower wing
tail supported by two open tail booms
engine, landing gear and useful-load in or attached to fuselage, fuel in gravity tank
airscrew :
fixed pitch 2 -bladed pusher airscrew with max. efficiency :0.60 [ ]
diameter airscrew 2.29 [m]
angle of attack prop : 9.88 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1100 [r.p.m.]
pitch at Max speed 0.94 [m]
blade-tip speed at Vmax and max revs. : 133 [m/s]
calculation : *1* (dimensions)
measured wing chord : 2.03 [m]
mean wing chord : 2.10 [m]
calculated wing chord (square tips): 2.16 [m]
Weights : main surfaces 180 lb = 81.6 kg, chassis : 250 lb = 113.4 kg, tail framing 40 lb = 18.1 kg, tail surfaces 55 lb = 24.9 kg, tail wheels 13 lb = 5.9 kg, vertical rudder 10 lb = 4.5 kg, elevator 32 lb = 14.5 kg, engine 320 lb = 145.2 kg, radiator&water 80 lb = 36.3 kg pilot 170 lb = 77.1 kg, a total 1150 lb = 522 kg
Area main surfaces 445 sq.ft. = 41.3 m2
wing aspect ratio : 4.76 []
estimated gap : 1.91 [m]
gap/chord : 0.91 [ ]
seize (span*length*height) : 352 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 0.9 [kg/hr]
fuel consumption(cruise speed) : 18.9 [kg/hr] (25.8 [litre/hr]) at 100 [%] power
distance flown for 1 kg fuel : 2.95 [km/kg] at 25 [m] cruise height, sfc : 508.8 [kg/kwh]
estimated total fuel capacity : 12.89 [litre] (9.44 [kg])
calculation : *3* (weight)
weight engine(s) dry : 95.0 [kg] = 2.55 [kg/KW]
weight 1.6 litre oil tank : 0.13 [kg]
oil tank filled with 0.3 litre oil : 0.3 [kg]
oil in engine 2.1 litre oil : 1.9 [kg]
fuel in engine 0.3 litre fuel : 0.19 [kg]
08 July 1908 Turin, Delagrange takes Mme. Therese Peltier in the air, the first woman passenger.
weight 0.8 litre gravity patrol tank(s) : 0.1 [kg]
weight radiator : 28.2 [kg]
weight exhaust pipes & fuel lines 4.2 [kg]
weight cowling 1.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 7.1 [kg]
total weight propulsion system : 138 [kg](24.5 [%])
***************************************************************
weight tail boom : 22 [kg]
fuselage skeleton (wood gauge : 4.91 [cm]): 65 [kg]
bracing : 5.0 [kg]
fuselage covering ( 13.5 [m2] doped linen fabric) : 4.3 [kg]
weight instruments. : 1.1 [kg]
weight controls : 5.1 [kg]
weight seats : 3.0 [kg]
weight engine mount : 1.9 [kg]
total weight fuselage : 85 [kg](15.1 [%])
***************************************************************
weight wing covering (doped linen fabric) : 33 [kg]
total weight ribs (22 ribs) : 34 [kg]
load on front upper spar (clmax) per running metre : 425.1 [N]
load on rear upper spar (vmax) per running metre : 127.2 [N]
total weight 8 spars : 22 [kg]
weight wings : 89 [kg]
weight wing/square meter : 2.12 [kg]
weight 8 interplane struts & cabane : 22.5 [kg]
weight cables (70 [m]) : 2.5 [kg] (= 35 [gram] per metre)
diameter cable : 2.4 [mm]
area of canard wing : 2.0 [m2
weight canard wing :4.4 [kg]
weight fin & rudder (1.2 [m2]) : 2.6 [kg]
weight stabilizer & elevator (4.0 [m2]): 8.8 [kg]
total weight wing surfaces & bracing : 130 [kg] (23.0 [%])
*******************************************************************
wielen naar verhouding erg licht
wheel pressure : 282.5 [kg]
weight 2 wheels (660 [mm] by 78 [mm]) : 12.3 [kg]
weight tailwheel(s) : 5.9 [kg]
weight undercarriage with axle 23.7 [kg]
total weight landing gear : 42.0 [kg] (7.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 396 [kg](70.0 [%])
weight oil for 0.6 hours flying : 0.6 [kg]
weight cooling fluids : 8.1 [kg]
calculated operational weight empty : 404 [kg] (71.5 [%])
published operational weight empty : 400 [kg] (70.8 [%])
_____________
| | o | |
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weight crew : 81 [kg]
weight fuel for 0.4 hours flying : 8 [kg]
********************************************************************
operational weight : 493 [kg](87.2 [%])
fuel reserve : 1.9 [kg] enough for 0.10 [hours] flying
possible additional useful load : 70 [kg]
operational weight fully loaded : 565 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 565 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 15.15 [kg/kW]
power loading (operational without useful load) : 13.22 [kg/kW]
total power : 37.3 [kW] at 1100 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.5 [g]
design flight time : 0.40 [hours]
design cycles : 1875 sorties, design hours : 750 [hours]
operational wing loading : 115 [N/m^2]
wing stress (3 g) during operation : 163 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.37 ["]
max. angle of attack (stalling angle) : 13.49 ["]
angle of attack at max. speed : 7.34 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.08 [ ]
lift coefficient at max. speed : 0.63 [ ]
induced drag coefficient at max. speed : 0.0479 [ ]
drag coefficient at max. speed : 0.1700 [ ]
drag coefficient (zero lift) : 0.1221 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 47 [km/u]
landing speed at sea-level: 50 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 52 [km/hr] at 25 [m] (power:77 [%])
min. power speed (max range) : 52 [km/hr] at 25 [m] (power:77 [%])
cruising speed : 56 [km/hr] op 25 [m] (power:83 [%])
design speed prop : 59 [km/hr]
maximum speed : 62 [km/hr] op 25 [m] (power:100 [%])
climbing speed at sea-level : 77 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 53.3 [km/u]
static prop wash : 61 [km/u]
take-off distance at sea-level : 91 [m]
lift/drag ratio : 4.15 [ ]
max. theoretical ceiling : 1578 [m] with flying weight :491 [kg] line 3370
climbing speed at 500m : 52.35 [m/min]
time to 500m : 8.25 [min]
Salon aeronautique 1908
climbing speed at 1000m : 27.63 [m/min]
time to 1000m : 26.35 [min]
published ceiling (25 [m]
practical ceiling (operational weight) : 1478 [m] with flying weight :493 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 748 [m] with flying weight :556 [kg]
turning speed at CLmax : 53.6 [km/u] at 50 [m] height
turn radius at 50m: 29 [m]
time needed for 360* turn 12.2 [seconds] at 50m
load factor at max. angle turn 1.27 ["g"]
calculation *10* (action radius & endurance)
operational endurance : 0.50 [hours] with 1 crew and 70.3 [kg] useful load and 100.0 [%] fuel
published endurance : 0.50 [hours] with 1 crew and possible useful load : 70.3 [kg] and 100.0 [%] fuel
maximum action radius : 118 [km] with 1 crew and 0 [kg] useful load ( 108.8 [litre] additional fuel needed)
max range theoretically with additional fuel tanks for total 108.8 [litre] fuel : 235.7 [km]
useful load with action-radius 250km : 0 [kg]
production (500 km) : 0 [tonkm/hour]
_
°_I>-/
Literature :
Jane’s record breaking aircraft page 256
Praktisch handbook vliegtuigen deel 1 page 44,45
Historische vliegtuigen page 169
https://de.wikipedia.org/wiki/L%C3%A9on_Delagrange
http://stephenesherman.com/voisin-delagrange-i-and-ii/
https://en.wikipedia.org/wiki/Voisin_1907_biplane
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 19 July 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4