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weight and performance calculations for the Benoist XIV
Benoist XIV
importance : ***
first flight : operational : 1 January 1914
country : United States of America
design : Thomas Benoist
production : 2 aircraft
general information :
On 1 January 1914 the world first scheduled airline service was opened with a heavier-than-air craft. A small Benoist flying boat, named “Lark of Duluth”, piloted by Roger Jannus flew between Tampa and St.Petersburg in Florida, a distance of 34.5 km and taking 1 passenger on each trip. At the first flight the major of St.Petersburg Abraham C. Pheil . The line was profitable, a 2 nd Benoist XIV with the name “Florida” was taken in service. However in April 1914, subsidies ceases, the end of the tourist season and the Mexican war ended the airline operations. In those few months 1205 passengers were carried over 17702 km.
users : Percival E. Fansler’s St.Petersburg – Tampa Airboat Line
crew : 1 passengers : 1
engine : 1 Roberts 6-X liquid-cooled 6 -cylinder inline engine 75 [hp](55.9 KW)
dimensions :
wingspan : 13.41 [m], length : 7.93 [m], height : 2.8[m]
wing area : 41.0 [m^2]
weights :
max.take-off weight : 800 [kg]
empty weight operational : 567 [kg] useful load : 100 [kg]
performance :
maximum speed :103 [km/hr] at sea-level
cruise speed :93 [km/u] op 100 [m]
service ceiling : 1500 [m]
range : 200 [km]
description :
3-bay biplane flying boat
2 (aid) tip floats
two spar upper and lower wing
engine in fuselage drives pusher propellor by chain
airscrew :
fixed pitch 2 -bladed pusher airscrew with max. efficiency :0.62 [ ]
diameter airscrew 3.05 [m]
angle of attack prop : 12.23 [ ]
fine pitch
reduction : 0.90 [ ]
airscrew revs : 1102 [r.p.m.]
pitch at Max speed 1.56 [m]
blade-tip speed at Vmax and max revs. : 178 [m/s]
calculation : *1* (dimensions)
measured wing chord : 1.63 [m]
mean wing chord : 1.53 [m]
calculated wing chord (square tips): 1.55 [m]
wing aspect ratio : 8.77 []
estimated gap : 1.73 [m]
gap/chord : 1.13 [ ]
seize (span*length*height) : 298 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 2.5 [kg/hr]
fuel consumption(cruise speed) : 16.1 [kg/hr] (22.0 [litre/hr]) at 81 [%] power
distance flown for 1 kg fuel : 5.74 [km/kg] at 750 [m] cruise height, sfc : 358.2 [kg/kwh]
estimated total fuel capacity : 53.91 [litre] (39.52 [kg])
calculation : *3* (weight)
weight engine(s) dry : 125.0 [kg] = 2.24 [kg/KW]
weight reduction gear : 2.8 [kg]
weight 8.7 litre oil tank : 0.74 [kg]
oil tank filled with 0.4 litre oil : 0.4 [kg]
oil in engine 3.1 litre oil : 2.8 [kg]
fuel in engine 0.4 litre fuel : 0.28 [kg]
weight 9.4 litre gravity patrol tank(s) : 1.4 [kg]
weight radiator : 8.0 [kg]
weight exhaust pipes & fuel lines 6.9 [kg]
weight cowling 2.2 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 20.6 [kg]
total weight propulsion system : 173 [kg](21.6 [%])
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fuselage skeleton (wood gauge : 5.18 [cm]): 55 [kg]
fuselage width : 1.12 [m]
cabin layout : pitch : 87 [cm] (1+1) seating
bracing : 3.8 [kg]
plywood/wood covering hull (gauche : 1.4 [cm]): 110 [kg]
Percival E. Fansler, Mayor Abraham C. Pheil, and Tony Jannus , the younger brother of Roger Jannus , with the Benoist Type XIV flying boat Lark of Duluth, 1 January 1914. (State Archives of Florida, Florida Memory)
weight instruments. : 1.1 [kg]
weight lighting : 1.1 [kg]
weight controls : 4.9 [kg]
weight seats : 6.0 [kg]
weight 45 [litre] main fuel tank empty : 3.6 [kg]
weight engine mounts & firewalls : 3 [kg]
total weight fuselage : 188 [kg](23.5 [%])
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weight wing covering (doped linen fabric) : 37 [kg]
total weight ribs (43 ribs) : 48 [kg]
load on front upper spar (clmax) per running metre : 499.4 [N]
load on rear upper spar (vmax) per running metre : 159.9 [N]
total weight 8 spars : 50 [kg]
weight wings : 135 [kg]
weight wing/square meter : 3.29 [kg]
weight 12 interplane struts & cabane : 24.8 [kg]
weight cables (93 [m]) : 7.3 [kg] (= 79 [gram] per metre)
diameter cable : 3.6 [mm]
weight fin & rudder (2.1 [m2]) : 7.2 [kg]
weight stabilizer & elevator (3.9 [m2]): 13.2 [kg]
total weight wing surfaces & bracing : 187 [kg] (23.4 [%])
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weight 2 tip floats : 11 [kg] (1.4 [%])
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calculated empty weight : 560 [kg](70.0 [%])
weight oil for 2.6 hours flying : 6.5 [kg]
weight cooling fluids : 12.1 [kg]
calculated operational weight empty : 578 [kg] (72.3 [%])
published operational weight empty : 567 [kg] (70.9 [%])
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weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 32 [kg]
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operational weight empty: 692 [kg](86.5 [%])
weight 1 passengers : 77 [kg]
weight luggage & freight : 23 [kg]
operational weight loaded: 792 [kg](86.5 [%])
fuel reserve : 7.2 [kg] enough for 0.45 [hours] flying
possible additional useful load : 1 [kg]
operational weight fully loaded : 800 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 800 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 14.30 [kg/kW]
power loading (operational without useful load) : 12.37 [kg/kW]
total power : 55.9 [kW] at 1225 [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 : 2.3 [g]
design flight time : 1.73 [hours]
design cycles : 579 sorties, design hours : 1000 [hours]
operational wing loading : 165 [N/m^2]
wing stress (3 g) during operation : 151 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.14 ["]
max. angle of attack (stalling angle) : 11.91 ["]
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 : 1.14 [ ]
lift coefficient at max. speed : 0.33 [ ]
induced drag coefficient at max. speed : 0.0072 [ ]
drag coefficient at max. speed : 0.0590 [ ]
drag coefficient (zero lift) : 0.0518 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 55 [km/u]
stalling speed at sea-level (MTOW): 60 [km/u]
landing speed at sea-level: 65 [km/hr]
min. drag speed (max endurance) : 65 [km/hr] at 750 [m](power :46 [%])
min. power speed (max range) : 74 [km/hr] at 750 [m] (power:51 [%])
max. rate of climb speed : 64.4 [km/hr] at sea-level
cruising speed : 93 [km/hr] op 750 [m] (power:73 [%])
design speed prop : 98 [km/hr]
maximum speed : 103 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level : 149 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 71.5 [km/u]
static prop wash : 89 [km/u]
take-off distance at sea-level : 78 [m]
lift/drag ratio : 8.65 [ ]
climb to 1000m with max payload : 11.39 [min]
climb to 2000m with max payload : 30.40 [min]
climb to 3000m with max payload : 63.24 [min]
published ceiling (1500 [m]
practical ceiling (operational weight) : 4068 [m] with flying weight :692 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 3328 [m] with flying weight :792 [kg]
max. dive speed : 235.1 [km/hr] at 2328 [m] height
turning speed at CLmax : 76.9 [km/u] at 50 [m] height
turn radius at 50m: 28 [m]
time needed for 360* turn 8.3 [seconds] at 50m
load factor at max. angle turn 1.92 ["g"]
calculation *10* (action radius & endurance)
published range : 200 [km] with 1 crew and 105.8 [kg] useful load and 88.1 [%] fuel
range : 233 [km] with 1 crew and 100.0 [kg] useful load and 102.8 [%] fuel
max range theoretically with additional fuel tanks for total 191.8 [litre] fuel : 807.8 [km]
useful load with range 500km : 54 [kg]
production : 4.97 [tonkm/hour]
oil and fuel consumption per tonkm : 3.76 [kg]
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Literature :
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
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(c) B van der Zalm 05 February 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4