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weight and performance calculations for the Deperdussin Model 1912

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The 1912 Deperdussin Monocoque racer and four of its pilots. From left to right:  Guillaume Busson ,  René Vidart ,  Jules Védrines  and  Maurice Prévost

Deperdussin Model 1912

importance : ****

first flight : operational : February 1912

country : France

design :

production : 1 prototype

general information :

Racing airplane with semi-monocoque fuselage. The fuselage had a box-girder skeleton covered with plywood. It was the first airplane to fly faster then 100 mph (161 km/h) in level flight. It used wing warping for lateral control. The wings were tapered with the chord at the tips greater than at the root. On 22 February 1912 Jules Vedrines succeeded in flying over 100 mph, he flew 200 km in 1 hr 15 min 20.8 secs, an average speed of 169 km/hr.

Speed records : 13 Jan 1912 Pau 145 km/h (100 hp Gnome engine), 22 feb 1912 Pau 161 km/h, 29 feb 1912 Pau 162 km/h, 01 Mar 1912 Pau 167 km/h, 02 Mar 1912 Pau 168 km/h, 13 Jul 1912 Reims 171 km/h 09 Sep 1912 Chicago 174 km/h. All records set by Jules Vedrines.

users : Guillaume Busson, René Vidart, Jules Védrines, Maurice Prévost

crew : 1

engine : 1 Gnome Double Gamma

air-cooled 14 -cylinder atmospheric inlet-valve rotary engine 140 [hp](104.4 KW)

dimensions :

wingspan : 7.0 [m], length : 7.0 [m], height : 2.3[m]

wing area : 11.6 [m^2]

weights :

max.take-off weight : 575 [kg]

empty weight operational : 400 [kg] useful load : 0 [kg]

performance :

maximum speed :174 [km/hr] at sea-level

cruise speed :157 [km/u] op 50 [m]

service ceiling : 1000 [m]

estimated action radius : 100 [km]

estimated endurance : 1.28 [hours]

description :

shoulder-winged 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 : 23.94 [ ]

reduction : 1.00 [ ]

airscrew revs : 1200 [r.p.m.]

pitch at Max speed 2.42 [m]

blade-tip speed at Vmax and max revs. : 153 [m/s]

Replica in the Old Rhinebeck Aerodrome, USA

calculation : *1* (dimensions)

wing chord : 1.47 [m]

mean wing chord : 1.66 [m]

wing aspect ratio : 4.22 [ ]

seize (span*length*height) : 113 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 9.4 [kg/hr]

fuel consumption(cruise speed) : 37.7 [kg/hr] (51.5 [litre/hr]) at 84 [%] power

distance flown for 1 kg fuel : 4.15 [km/kg] at 500 [m] cruise height, sfc : 430.0 [kg/kwh]

estimated total fuel capacity : 74.59 [litre] (54.68 [kg])

calculation : *3* (weight)

weight engine(s) dry : 193.1 [kg] = 1.85 [kg/KW]

weight 18.7 litre oil tank : 1.59 [kg]

oil tank filled with 0.8 litre oil : 0.7 [kg]

oil in engine 0.6 litre oil : 0.5 [kg]

fuel in engine 0.7 litre fuel : 0.52 [kg]

weight 21.9 litre gravity patrol tank(s) : 3.3 [kg]

Deperdussin racer in the Musee de l’air and l’espace, Paris, Le Bourget

weight cowling 4.2 [kg]

weight airscrew(s) (wood) incl. boss & bolts : 12.7 [kg]

total weight propulsion system : 215 [kg](37.4 [%])

***************************************************************

fuselage skeleton (wood gauge : 5.04 [cm]): 45 [kg]

bracing : 2.2 [kg]

fuselage covering ( 9.3 [m2] doped linen fabric) : 3.0 [kg]

weight instruments. : 1.1 [kg]

weight controls : 3.8 [kg]

weight seats : 3.0 [kg]

weight 53 [litre] main fuel tank empty : 4.2 [kg]

weight engine mount : 5.2 [kg]

total weight fuselage : 68 [kg](11.8 [%])

***************************************************************

weight wing covering (doped linen fabric) : 9 [kg]

total weight ribs (28 ribs) : 34 [kg]

load on front upper spar (clmax) per running metre : 716.0 [N]

load on rear upper spar (vmax) per running metre : 236.9 [N]

total weight 4 spars : 20 [kg]

weight wings : 63 [kg]

weight wing/square meter : 5.45 [kg]

weight cables (28 [m]) : 4.7 [kg] (= 168 [gram] per metre)

diameter cable : 5.2 [mm]

weight fin & rudder (0.6 [m2]) : 3.2 [kg]

weight stabilizer & elevator (1.3 [m2]): 7.2 [kg]

total weight wing surfaces & bracing : 78 [kg] (13.6 [%])

*******************************************************************

wheel pressure : 287.5 [kg]

weight 2 wheels (700 [mm] by 82 [mm]) : 12.8 [kg]

weight tailskid : 1.5 [kg]

weight undercarriage with axle 19.2 [kg]

total weight landing gear : 33.5 [kg] (5.8 [%]

*******************************************************************

Length : 20 ft 5 in = 6.22 [m]

Span : 23 ft = 7.01 [m]

********************************************************************

calculated empty weight : 395 [kg](68.7 [%])

weight oil for 1.5 hours flying : 14.4 [kg]

calculated operational weight empty : 409 [kg] (71.2 [%])

published operational weight empty : 400 [kg] (69.6 [%])

---o---

"

weight crew : 81 [kg]

weight fuel for 1.0 hours flying : 38 [kg]

********************************************************************

operational weight : 528 [kg](91.8 [%])

fuel reserve : 17.0 [kg] enough for 0.45 [hours] flying

possible additional useful load : 30 [kg]

operational weight fully loaded : 575 [kg] with fuel tank filled for 100 [%]

published maximum take-off weight : 575 [kg] (100.0 [%])

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calculation : * 4 * (engine power)

power loading (Take-off) : 5.51 [kg/kW]

power loading (operational without useful load) : 5.06 [kg/kW]

total power : 104.4 [kW] at 1200 [r.p.m]

calculation : *5* (loads)

manoeuvre load : 1.8 [g] at 1000 [m]

limit load : 3.5 [g] ultimate load : 5.2 [g] load factor : 2.3 [g]

design flight time : 1.02 [hours]

design cycles : 705 sorties, design hours : 720 [hours]

operational wing loading : 446 [N/m^2]

wing stress (3 g) during operation : 246 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.44 ["]

max. angle of attack (stalling angle) : 13.66 ["]

angle of attack at max. speed : 3.07 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° :0.10 [ ]

lift coefficient at max. angle of attack : 1.05 [ ]

lift coefficient at max. speed : 0.31 [ ]

induced drag coefficient at max. speed : 0.0099 [ ]

drag coefficient at max. speed : 0.0800 [ ]

drag coefficient (zero lift) : 0.0701 [ ]

calculation : *8* (speeds

stalling speed at sea-level (OW): 95 [km/u]

stalling speed at sea-level (MTOW): 99 [km/u]

landing speed at sea-level: 112 [km/hr]

min. drag speed (max endurance) : 109 [km/hr] at 500 [m](power :46 [%])

min. power speed (max range) : 125 [km/hr] at 500 [m] (power:52 [%])

max. rate of climb speed : 109.0 [km/hr] at sea-level

cruising speed : 157 [km/hr] op 500 [m] (power:75 [%])

design speed prop : 165 [km/hr]

maximum speed : 174 [km/hr] op 50 [m] (power:99 [%])

climbing speed at sea-level : 355 [m/min]

calculation : *9* (regarding various performances)

take-off speed : 113.9 [km/u]

static prop wash : 45 [km/u]

take-off distance at sea-level : 284 [m]

lift/drag ratio : 5.96 [ ]

time to 1000m : 3.39 [min]

time to 2000m : 8.27 [min]

time to 3000m : 15.11 [min]

practical ceiling (operational weight) : 4333 [m] with flying weight :528 [kg] line 3385

practical ceiling fully loaded (mtow- 30 min.fuel) : 4033 [m] with flying weight :556 [kg]

turning speed at CLmax : 130.8 [km/u] at 50 [m] height

turn radius at 50m: 84 [m]

time needed for 360* turn 14.5 [seconds] at 50m

load factor at max. angle turn 1.89 ["g"]

calculation *10* (action radius & endurance)

estimated endurance : 1.28 [hours] with 1 crew and possible useful load : 36.6 [kg] and 88.1 [%] fuel

published range : 200 [km] with 1 crew and 36.6 [kg] useful load and 88.1 [%] fuel

max range theoretically with additional fuel tanks for total 115.7 [litre] fuel : 352.1 [km]

useful load with range 500km : 0 [kg]

production (500 km) : 0 [tonkm/hour]

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Literature :

Jane’s record breaking aircraft

Historische vliegtuigen

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