AIRCRAFT INVESTIGATION
weight and performance calculations for the Deperdussin Model 1913
Deperdussin Model 1913 Corsa “Monocoque”
role : racing aircraft
importance : ****
first flight : operational : June 1913
country : France
design : Louis Bechérau
production : 1 prototype
general information :
The 1913 model had a 100% monocoque fuselage of plywood. It was developed from the 1912 model that still had a semi-monocoque hull. The monocoque was lighter, stronger and aerodynamically better than a conventional tube frame-cloth fuselage.
On September 29, 1913, Maurice Prévost established a new world speed record during the Gordon Bennet Trophy at Reims with a speed of 203,850 km/h, becoming the first human to fly faster than 200 km/h.
That same year, however, Armand Deperdussin was arrested for embezzlement. His company was acquired by Louis Bleriot and eventually called Société Pour L'Aviation et ses Derives (S.P.A.D.). This company would build several excellent fighter aircraft during WWI.
The Suisse engineer Eugene Ruchonnet (187-1912) was the first who came on the thought of making the hull skin "bearing ". The principle of wearing skin (monocoque) was thus already known in the early years of aviation. It is therefore surprising that this technique was only actually and widely applied much later (Douglas DC-3). Probably this was due to a lack of suitable material: aluminium.
Speed records : 17 June 1913 179.8 km/h, 27 Sep 1913 191.9 km/h 29 Sep 1913 203.8 km/h all 3 times flown by Maurice Prevost in Reims.
2-bladed Chauviere propellor, 2.31m diameter
construction : ashwood, covered with triplex and linen fabric.
users : Maurice Prévost
crew : 1
engine : 1 Gnome Double Lambda air-cooled 14 -cylinder atmospheric inlet-valve rotary engine 160 [hp](119.3 KW)
dimensions :
wingspan : 6.65 [m], length : 6.09 [m], height : 2.28[m]
wing area : 9.66 [m^2]
weights :
max.take-off weight : 612 [kg]
empty weight operational : 450 [kg] useful load : 0 [kg]
performance :
maximum speed :209 [km/hr] at sea-level
cruise speed :188 [km/u] op 50 [m]
service ceiling : 1000 [m]
range : 225 [km]
estimated endurance : 1.20 [hours]
description :
medium-wing monoplane 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 tractor airscrew with max. efficiency :0.62 [ ]
diameter airscrew 2.31 [m]
angle of attack prop : 27.11 [ ]
coarse pitch
reduction : 1.00 [ ]
airscrew revs : 1250 [r.p.m.]
pitch at Max speed 2.79 [m]
blade-tip speed at Vmax and max revs. : 162 [m/s]
calculation : *1* (dimensions)
wing chord : 1.60 [m]
mean wing chord : 1.45 [m]
wing aspect ratio : 4.58 []
seize (span*length*height) : 92 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 11.9 [kg/hr]
fuel consumption(cruise speed) : 50.2 [kg/hr] (68.4 [litre/hr]) at 83 [%] power
distance flown for 1 kg fuel : 3.75 [km/kg] at 500 [m] cruise height, sfc : 506.0 [kg/kwh]
estimated total fuel capacity : 92.91 [litre] (68.10 [kg])
calculation : *3* (weight)
weight engine(s) dry : 208.8 [kg] = 1.75 [kg/KW]
weight 22.1 litre oil tank : 1.88 [kg]
oil tank filled with 0.9 litre oil : 0.8 [kg]
oil in engine 0.7 litre oil : 0.6 [kg]
fuel in engine 0.8 litre fuel : 0.60 [kg]
weight 29.1 litre gravity patrol tank(s) : 4.4 [kg]
weight cowling 4.8 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 13.9 [kg]
total weight propulsion system : 234 [kg](38.2 [%])
***************************************************************
fuselage skeleton (wood gauge : 5.89 [cm]): 54 [kg]
bracing : 2.3 [kg]
fuselage covering ( 7.0 [m2] doped linen fabric) : 2.2 [kg]
weight instruments. : 1.1 [kg]
weight controls : 3.5 [kg]
weight seats : 3.0 [kg]
weight 64 [litre] main fuel tank empty : 5.1 [kg]
weight engine mount : 6.0 [kg]
total weight fuselage : 77 [kg](12.6 [%])
***************************************************************
weight wing covering (doped linen fabric) : 9 [kg]
total weight ribs (34 ribs) : 36 [kg]
load on front upper spar (clmax) per running metre : 1058.0 [N]
load on rear upper spar (vmax) per running metre : 272.5 [N]
total weight 4 spars : 27 [kg]
weight wings : 73 [kg]
weight wing/square meter : 7.51 [kg]
weight cables (27 [m]) : 5.9 [kg] (= 223 [gram] per metre)
diameter cable : 6.0 [mm]
weight fin & rudder (0.5 [m2]) : 3.9 [kg]
weight stabilizer & elevator (1.1 [m2]): 8.2 [kg]
total weight wing surfaces & bracing : 91 [kg] (14.8 [%])
*******************************************************************
wheel pressure : 306.0 [kg]
weight 2 wheels (650 [mm] by 76 [mm]) : 13.6 [kg]
weight tailskid : 2.0 [kg]
weight undercarriage with axle 25.1 [kg]
total weight landing gear : 40.7 [kg] (6.7 [%]
*******************************************************************
********************************************************************
calculated empty weight : 443 [kg](72.3 [%])
weight oil for 1.4 hours flying : 17.1 [kg]
calculated operational weight empty : 460 [kg] (75.1 [%])
published operational weight empty : 450 [kg] (73.5 [%])
___o___
"
weight crew : 81 [kg]
weight fuel for 1.0 hours flying : 50 [kg]
********************************************************************
operational weight : 591 [kg](96.5 [%])
fuel reserve : 17.9 [kg] enough for 0.36 [hours] flying
possible additional useful load : 3 [kg]
operational weight fully loaded : 612 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 612 [kg] (100.0 [%])
||
I||==|
||
calculation : * 4 * (engine power)
power loading (Take-off) : 5.13 [kg/kW]
power loading (operational without useful load) : 4.95 [kg/kW]
total power : 119.3 [kW] at 1250 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.0 [g] at 1000 [m]
limit load : 3.5 [g] ultimate load : 5.2 [g] load factor : 2.9 [g]
design flight time : 0.96 [hours]
design cycles : 1202 sorties, design hours : 1150 [hours]
operational wing loading : 600 [N/m^2]
wing stress (3 g) during operation : 240 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.39 ["]
max. angle of attack (stalling angle) : 13.55 ["]
angle of attack at max. speed : 2.67 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.07 [ ]
lift coefficient at max. speed : 0.29 [ ]
induced drag coefficient at max. speed : 0.0079 [ ]
drag coefficient at max. speed : 0.0636 [ ]
drag coefficient (zero lift) : 0.0557 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 109 [km/u]
stalling speed at sea-level (MTOW): 111 [km/u]
landing speed at sea-level: 128 [km/hr]
min. drag speed (max endurance) : 131 [km/hr] at 500 [m](power :46 [%])
min. power speed (max range) : 148 [km/hr] at 500 [m] (power:51 [%])
max. rate of climb speed : 131.0 [km/hr] at sea-level
cruising speed : 188 [km/hr] op 500 [m] (power:75 [%])
design speed prop : 199 [km/hr]
maximum speed : 209 [km/hr] op 50 [m] (power:99 [%])
climbing speed at sea-level : 364 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 127.3 [km/u]
static prop wash : 45 [km/u]
take-off distance at sea-level : 347 [m]
time to 1000m : 3.42 [min]
time to 2000m : 8.82 [min]
climb to 3000m : 17.40 [min]
published ceiling (1000 [m]
practical ceiling (operational weight) : 3723 [m] with flying weight :591 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 3723 [m] with flying weight :587 [kg]
max. dive speed : 438.9 [km/hr] at 2723 [m] height
turning speed at CLmax : 150.0 [km/u] at 50 [m] height
turn radius at 50m: 110 [m]
time needed for 360* turn 16.6 [seconds] at 50m
load factor at max. angle turn 1.89 ["g"]
calculation *10* (action radius & endurance)
estimated endurance : 1.20 [hours] with 1 crew and possible useful load : 11.3 [kg] and 88.1 [%] fuel
published range : 225 [km] with 1 crew and 11.3 [kg] useful load and 88.1 [%] fuel
max range theoretically with additional fuel tanks for total 97.3 [litre] fuel : 267.5 [km]
useful load with range 500km : 0 [kg]
production (500 km) : 0 [tonkm/hour]
Literature :
Jane’s record breaking aircraft page 31
Praktisch handbook vliegtuigen deel I page 92
Historische vliegtuigen page 73,
Jane’s Fighting aircraft WWI page 109
http://www.pilotfriend.com/photo_albums/timeline/deperdussin.htm
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 07 October 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4