Bleriot XIbis
role : single seat scout
first flight : 1911 operational : October 1911
country : France
design :
production : unknown
general information :
The Bleriot type XI was used by the French and Italian army for
reconnaissance. These were improved version of the XI and fitted with a more
powerful 50 hp engine. On 23 October 1911 the first operational military flight
was performed by Captain Piazza during the Italian-Turkish war in North-Africa.
He flew in his XIbis from Tripoli to Azizia (32°39’N,13°04’E), a distance of 43 km to
observe the movements of the Turkish army.
Pegoud made the first looping’s in a single-seat XI, very similar to the XIbis.
On 23 September 1910 the young Peruvian pilot George Chavez flew for the first
time across the alps.
users : France, Italy
crew : 1
armament : no fixed armament
engine : 1 Gnome 7 Omega air-cooled 7 -cylinder atmospheric inlet-valve rotary engine 50 [hp](36.8 KW)
dimensions :
wingspan : 8.9 [m], length : 7.8 [m], height : 2.6[m]
wing area : 15.0 [m^2]
weights :
max.take-off weight : 385 [kg]
empty weight operational (estimation): 230.0 [kg] bombload : 25 [kg]
performance :
maximum speed : 110 [km/u] op 1000 [m]
service ceiling : 3000 [m]
endurance : 2.0 [hours]
estimated action radius : 99 [km]
description :
shoulder-winged monoplane with fixed landing gear and tail strut
two spar wing
engines, landing gear, fuel and bombs in or attached to the fuselage
The famous French flyer Adolphe Pegoud flew a Bleriot XI, this plane is still preserved and can be seen in the Musee de l’air in Paris (Le Bourget). Pegouds aerobatic flights were known in many countries. He performed on 21 September 1913 as one of the first a looping in a single-seat XI.
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.61 [ ]
estimated diameter airscrew 2.15 [m]
angle of attack prop : 17.47 [ ]
reduction : 1.00 [ ]
airscrew revs : 1150 [r.p.m.]
pitch at Max speed 1.59 [m]
blade-tip speed at Vmax and max revs. : 133 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.69 [m]
calculated wing chord (rounded tips): 2.19 [m]
wing aspect ratio : 5.28 []
gap : 0.00 [m]
gap/chord : 0.00 [ ]
seize (span*length*height) : 180 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.3 [kg/hr]
fuel consumption(cruise speed) : 13.6 [kg/hr] (18.5 [litre/hr]) at 70 [%] power
distance flown for 1 kg fuel : 7.30 [km/kg]
estimated total fuel capacity : 42 [litre] (31 [kg])
A XI replica
calculation : *3* (weight)
weight engine(s) dry : 75.0 [kg] = 2.04 [kg/KW]
weight 10 litre oil tank : 0.8 [kg]
oil tank filled with 0.3 litre oil : 0.2 [kg]
oil in engine 0 litre oil : 0.2 [kg]
fuel in engine 0 litre fuel : 0.2 [kg]
weight 8 litre gravity patrol tank(s) : 1.2 [kg]
weight cowling 1.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 8.5 [kg]
total weight propulsion system : 87 [kg](22.5 [%])
***************************************************************
fuselage skeleton (wood gauge : 4.11 [cm]): 34 [kg]
bracing : 1.9 [kg]
fuselage covering ( 11.5 [m2] doped linen fabric) : 3.7 [kg]
weight controls + indicators: 5.8 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 1.8 [kg]
weight 34 [litre] main fuel tank empty : 2.7 [kg]
weight engine mounts & firewalls : 2 [kg]
total weight fuselage : 59 [kg](15.4 [%])
***************************************************************
weight wing covering (doped linen fabric) : 10 [kg]
total weight ribs (19 ribs) : 23 [kg]
load on front upper spar (clmax) per running metre : 346.6 [N]
load on rear upper spar (vmax) per running metre : 115.4 [N]
total weight 4 spars : 16 [kg]
weight wings : 48 [kg]
weight wing/square meter : 3.21 [kg]
weight cables (36 [m]) : 4.7 [kg] (= 131 [gram] per metre)
diameter cable : 4.6 [mm]
weight fin & rudder (0.9 [m2]) : 3.1 [kg]
weight stabilizer & elevator (1.7 [m2]): 5.5 [kg]
total weight wing surfaces & bracing : 62 [kg] (16.0 [%])
*******************************************************************
weight armament : 0 [kg]
********************************************************************
Probably Anthony Fokker saw Pegoud flying over Johannisthal in his Bleriot XI. The aerobatics Pegoud made, Fokker could not do with his stabile Spin monoplane. Fokker bought a second hand Morane Saulnier H and from this he developed the Fokker M.5 in which Fokker could perform the same aerobatics.
wheel pressure : 192.5 [kg]
weight 2 wheels (600 [mm] by 71 [mm]) : 9.3 [kg]
weight tailskid : 1.0 [kg]
weight undercarriage with axle 10.1 [kg]
total weight landing gear : 20.4 [kg] (5.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 228 [kg](59.2 [%])
weight oil for 2.4 hours flying : 7.9 [kg]
*******************************************************************
calculated operational weight empty : 236 [kg] (61.3 [%])
estimated operational weight empty : 230 [kg] (59.7 [%])
---o---
"
weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 27 [kg]
********************************************************************
operational weight : 344 [kg](89.4 [%])
bomb load : 25 [kg]
operational weight bombing mission : 369 [kg]
fuel reserve : 4 [kg] enough for 0.27 [hours] flying
possible additional useful load : 12 [kg]
operational weight fully loaded : 385 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 385 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 9.36 [kg/kW]
total power : 36.8 [kW] at 1150 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.6 [g] at 1000 [m]
limit load : 3.75 [g] ultimate load : 5.6 [g] load factor : 2.3 [g]
design flight time : 1.60 [hours]
design cycles : 484 sorties, design hours : 775 [hours]
operational wing loading : 225 [N/m^2]
wing stress (3 g) during operation : 210 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.32 ["]
max.angle of attack (stalling angle) : 13.30 ["]
angle of attack at max.speed : 4.40 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.11 [ ]
lift coefficient at max.speed : 0.43 [ ]
induced drag coefficient at max.speed : 0.0151 [ ]
drag coefficient at max.speed : 0.0803 [ ]
drag coefficient (zero lift) : 0.0652 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 66 [km/u]
landing speed at sea-level (OW without bombload): 79 [km/hr]
min.drag speed (max endurance) : 78 [km/hr] at 1500 [m](power :50 [%])
min. power speed (max range) : 90 [km/hr] at 1500 [m] (power:58 [%])
max.rate of climb speed : 72.3 [km/hr] at sea-level
cruising speed : 99 [km/hr] op 1500 [m] (power:66 [%])
design speed prop : 104 [km/hr]
maximum speed : 110 [km/hr] op 1000 [m] (power:85 [%])
climbing speed at sea-level (without bombload) : 189 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 190 [m]
lift/drag ratio : 6.91 [ ]
max. practical ceiling : 3275 [m] with flying weight :324 [kg]
practical ceiling (operational weight): 2975 [m] with flying weight :344 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2575 [m] with flying weight :371 [kg]
published ceiling (3000 [m]
climb to 1500m (without bombload) : 9.53 [min]
max.dive speed : 246.1 [km/hr] at 1575 [m] height
load factor at max.angle turn 1.68 ["g"]
turn radius at 500m: 44 [m]
time needed for 360* turn 11.5 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.27 [hours] with 1 crew and 37 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 2.00 [hours] with 1 crew and possible useful (bomb) load : 41 [kg] and 88.1 [%] fuel
action radius : 175 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 93 [litre] fuel : 496 [km]
useful load with action-radius 250km : 0 [kg]
production (500 km) : 0 [tonkm/hour]
I-°=/
°
Literature :
Bombers 1914-19 blz.17,97
Fighting aircraft WOI blz.103
Historische vliegtuigen blz.107
Praktisch handboek vliegtuigen deel 1 blz.162
They fought for the sky page 35
Warplanes page 7
Jane’s fighting aircraft WWI page 216f
last check python :
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 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.2(32-bit)