AIRCRAFT INVESTIGATION
weight and performance calculations for the Fabre Hydravion
Fabre Hydravion
importance : ****
first flight : 28 March 1910 operational : March 1910
country : France
design : Henri Fabre
production : 1 prototype
general information :
The Hydravion designed by Henri Fabre was the first aircraft that could take of from the water and sustain flight. On 28 March 1910 Fabre succeeded to take of from the water in the harbour of La Mede near to Marseille. After a take-off run of 300m it came loose from the water and flew for 540m at a hight of 2m and landed safely.
On 29 March it made a flight of 6km
Fabre continued to make flights with the sea-plane till 12 April 1911 when it was damaged beyond reparation on landing by Jean Bécue near to the shore of Monaco .
Lateral control was by wing warping.
users : Henri Fabre
crew : 1
engine : 1 Gnome 7 Omega air-cooled 7 -cylinder atmospheric inlet-valve rotary engine 50 [hp](37.3 KW)
dimensions :
wingspan : 14.0 [m], length : 8.5 [m], height : 3.7[m]
wing area : 17.0 [m^2]
weights :
max.take-off weight : 475 [kg]
empty weight operational : 380 [kg] useful load : 0 [kg]
performance :
maximum speed :89 [km/hr] at sea-level
cruise speed :80 [km/u] op 20 [m]
service ceiling : 500 [m]
estimated action radius : 25 [km]
estimated endurance : 0.62 [hours]
description :
shoulder-winged monoplane two float with nose float
no tip floats
mono spar wing
engine, landing gear and useful-load in or attached to fuselage, fuel in gravity tank
airscrew :
fixed pitch 2 -bladed pusher Chauviere airscrew with max. efficiency :0.61 [ ]
diameter airscrew 2.40 [m]
angle of attack prop : 14.70 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1200 [r.p.m.]
pitch at Max speed 1.24 [m]
blade-tip speed at Vmax and max revs. : 128 [m/s]
calculation : *1* (dimensions)
measured wing chord : 1.30 [m]
mean wing chord : 1.21 [m]
calculated wing chord (rounded leading edge tips): 1.28 [m]
wing aspect ratio : 11.53 []
seize (span*length*height) : 440 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 3.4 [kg/hr]
fuel consumption(cruise speed) : 16.0 [kg/hr] (21.9 [litre/hr]) at 87 [%] power
distance flown for 1 kg fuel : 5.00 [km/kg] at 250 [m] cruise height, sfc : 497.0 [kg/kwh]
estimated total fuel capacity : 15.50 [litre] (11.36 [kg])
calculation : *3* (weight)
weight engine(s) dry : 75.0 [kg] = 2.01 [kg/KW]
weight 3.7 litre oil tank : 0.32 [kg]
oil tank filled with 0.3 litre oil : 0.3 [kg]
oil in engine 0.2 litre oil : 0.2 [kg]
fuel in engine 0.3 litre fuel : 0.19 [kg]
weight 15.5 litre gravity patrol tank(s) : 2.3 [kg]
weight cowling 1.5 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 21.8 [kg]
total weight propulsion system : 101 [kg](21.3 [%])
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fuselage skeleton (wood gauge : 5.03 [cm]): 48 [kg]
bracing : 2.6 [kg]
weight instruments. : 1.1 [kg]
weight controls : 4.9 [kg]
weight seats : 3.0 [kg]
weight engine mount : 1.9 [kg]
total weight fuselage : 62 [kg](13.0 [%])
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weight wing covering (doped linen fabric) : 15 [kg]
total weight ribs (32 ribs) : 28 [kg]
load on front upper spar (clmax) per running metre : 357.9 [N]
total weight 4 spars : 40 [kg]
weight wings : 84 [kg]
weight wing/square meter : 4.93 [kg]
weight cables (56 [m]) : 18.8 [kg] (= 335 [gram] per metre)
diameter cable : 7.4 [mm]
weight fin & rudder (2.7 [m2]) : 13.9 [kg]
weight stabilizer & elevator (1.9 [m2]): 9.6 [kg]
total weight wing surfaces & bracing : 126 [kg] (26.5 [%])
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0
weight floats : 90 [kg] (19.0 [%])
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calculated empty weight : 379 [kg](79.8 [%])
weight oil for 0.7 hours flying : 2.5 [kg]
calculated operational weight empty : 382 [kg] (80.3 [%])
published operational weight empty : 380 [kg] (80.0 [%])
---o---
"
weight crew : 81 [kg]
weight fuel for 0.5 hours flying : 8 [kg]
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operational weight : 471 [kg](99.1 [%])
fuel reserve : 3.3 [kg] enough for 0.21 [hours] flying
possible additional useful load : 1 [kg]
operational weight fully loaded : 475 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 475 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 12.74 [kg/kW]
power loading (operational without useful load) : 12.62 [kg/kW]
total power : 37.3 [kW] at 1200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 0.8 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.7 [g]
design flight time : 0.50 [hours]
design cycles : 668 sorties, design hours : 100 [hours]
operational wing loading : 272 [N/m^2]
wing stress (3 g) during operation : 165 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.08 ["]
max. angle of attack (stalling angle) : 10.73 ["]
angle of attack at max. speed : 6.79 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.09 [ ]
lift coefficient at max. speed : 0.73 [ ]
induced drag coefficient at max. speed : 0.0194 [ ]
drag coefficient at max. speed : 0.1439 [ ]
drag coefficient (zero lift) : 0.1245 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 73 [km/u]
stalling speed at sea-level (MTOW): 73 [km/u]
landing speed at sea-level: 85 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 81 [km/hr] at 250 [m] (power:78 [%])
min. power speed (max range) : 81 [km/hr] at 250 [m] (power:78 [%])
cruising speed : 80 [km/hr] op 250 [m] (power:77 [%])
design speed prop : 85 [km/hr]
maximum speed : 89 [km/hr] op 20 [m] (power:100 [%])
climbing speed at sea-level : 103 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 80.2 [km/u]
static prop wash : 69 [km/u]
take-off distance at sea-level : 210 [m]
lift/drag ratio : 7.39 [ ]
time to 1000m : 15.32 [min]
time to 1500m : 33.44 [min]
practical ceiling (operational weight) : 1978 [m] with flying weight :471 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 1978 [m] with flying weight :467 [kg]
max. dive speed : 196.0 [km/hr] at 978 [m] height
turning speed at CLmax : 84.5 [km/u] at 50 [m] height
turn radius at 50m: 62 [m]
time needed for 360* turn 16.6 [seconds] at 50m
load factor at max. angle turn 1.35 ["g"]
calculation *10* (action radius & endurance)
estimated endurance : 0.62 [hours] with 1 crew and possible useful load : 2.3 [kg] and 88.1 [%] fuel
maximum action radius : 31 [km] with 1 crew and 0 [kg] useful load ( 16.8 [litre] additional fuel needed)
max range theoretically with additional fuel tanks for total 16.8 [litre] fuel : 61.7 [km]
useful load with range 500km : 0 [kg]
production (500 km) : 0 [tonkm/hour]
I-°=/
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Literature :
Praktisch handbook vliegtuigen deel 1 page 76
Historische vliegtuigen page 131
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 07 October 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4