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weight and performance calculations for the Curtiss H-16
Curtiss H-16
role : maritime patrol, ASW
importance : ***
first flight : operational : May 1918
country : United States of America
design :
production : 150 aircraft
general information :
The RNAS received 71 H-12 and 75 H-16 flying boats commencing operations over the North Sea April 1917. The RNAS H-16 had Rolls Royce Eagle IV engines. The US Navy H-16’s used Liberty engines. Chord : 2.15m gap : 2.45m
Fuel : max. 410 US gallon = 1552 litre
users : RNAS, US Navy
crew : 4
armament : 5 movable 7.70 [mm] (0.303 in) Lewis MK.III machine-guns
engine : 2 Rolls Royce Eagle VIII liquid-cooled 12 -cylinder V-engine 375 [hp](275.8 KW) (RNAS) or 2 Liberty 12 400 hp engines (US Navy)
dimensions :
wingspan : 28.97 [m], length : 14.05 [m], height : 5.39[m]
wing area : 108.13 [m^2]
weights :
max.take-off weight : 5889 [kg]
empty weight operational (estimation): 3700.1 [kg] bombload : 420 [kg]
performance :
maximum speed : 140 [km/u] op 610 [m]
climbing speed : 122 [m/min]
service ceiling : 3810 [m]
endurance : 8.945 [hours]
estimated action radius : 564 [km]
description :
4-bay biplane flying boat
2 (aid) tip floats
upper wingtips supported by slanted flying wires
two spar upper and lower wing
engines attached to the wings , landing gear, fuel and bombload in or attached to
fuselage
airscrew :
two fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.64 [ ]
estimated diameter airscrew 2.92 [m]
angle of attack prop : 16.17 [ ]
reduction : 0.60 [ ]
airscrew revs : 1170 [r.p.m.]
pitch at Max speed 1.99 [m]
blade-tip speed at Vmax and max revs. : 183 [m/s]
calculation : *1* (dimensions)
mean wing chord : 2.07 [m]
calculated wing chord (rounded tips): 2.20 [m]
wing aspect ratio : 13.97 []
gap : 2.45 [m]
gap/chord : 1.18 [ ]
seize (span*length*height) : 2194 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 8.3 [kg/hr]
fuel consumption(cruise speed) : 112.1 [kg/hr] (152.9 [litre/hr]) at 64 [%] power
distance flown for 1 kg fuel : 1.12 [km/kg]
estimated total fuel capacity : 1552 [litre] (1138 [kg])
calculation : *3* (weight)
weight engine(s) dry : 816.4 [kg] = 1.48 [kg/KW]
weight reduction gear : 60.7 [kg]
weight 113 litre oil tank : 9.6 [kg]
oil tank filled with 4.1 litre oil : 3.7 [kg]
oil in engine 31 litre oil : 27.6 [kg]
fuel in engine 4 litre fuel : 2.8 [kg]
weight 65 litre gravity patrol tank(s) : 9.7 [kg]
weight radiator : 79.0 [kg]
weight exhaust pipes & fuel lines 39.8 [kg]
weight self-starter : 6.8 [kg]
weight cowling 11.0 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 82.7 [kg]
total weight propulsion system : 1201 [kg](20.4 [%])
***************************************************************
fuselage skeleton (wood gauge : 10.41 [cm]): 390 [kg]
bracing : 48.3 [kg]
plywood/wood covering hull (gauche : 1.2 [cm]): 293.7 [kg]
weight controls + indicators: 10.0 [kg]
weight seats : 12.0 [kg]
weight other details, lighting set, etc. : 9.1 [kg]
weight bomb storage : 29.4 [kg]
weight two 744 [litre] main fuel tanks empty : 119.0 [kg]
weight interior + equipment + fuel lines: 76 [kg]
total weight fuselage : 987 [kg](16.8 [%])
***************************************************************
weight wing covering (doped linen fabric) : 69 [kg]
total weight ribs (232 ribs) : 350 [kg]
weight engine mounts : 28 [kg]
load on front upper spar (clmax) per running metre : 870.0 [N]
load on rear upper spar (vmax) per running metre : 552.1 [N]
total weight 8 spars : 336 [kg]
weight wings : 755 [kg]
weight wing/square meter : 6.98 [kg]
weight 16 interplane struts & cabane : 154.8 [kg]
weight cables (168 [m]) : 88.8 [kg] (= 529 [gram] per metre)
diameter cable : 9.3 [mm]
weight fin & rudder (9.7 [m2]) : 69.5 [kg]
weight stabilizer & elevator (12.2 [m2]): 85.7 [kg]
total weight wing surfaces & bracing : 1181 [kg] (20.1 [%])
*******************************************************************
weight machine-gun(s) : 65.0 [kg]
weight pivot mounting mg :30.0 [kg]
weight armament : 95 [kg]
********************************************************************
weight 2 tip floats : 76 [kg] (1.3 [%])
*******************************************************************
********************************************************************
calculated empty weight : 3540 [kg](60.1 [%])
weight oil for 10.7 hours flying : 88.8 [kg]
weight cooling fluids : 119.2 [kg]
weight 20 drums empty : 8.6 [kg]
weight ammunition (1940 rounds) : 61.8 [kg]
weight signal pistol with cartridges : 3.6 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 3814 [kg] (64.8 [%])
estimated operational weight empty : 3700 [kg] (62.8 [%])
_____________
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~U~
weight crew : 324 [kg]
weight fuel for 2.0 hours flying : 224 [kg]
********************************************************************
operational weight : 4362 [kg](74.1 [%])
bomb load : 420 [kg]
operational weight bombing mission : 4782 [kg]
fuel reserve : 914 [kg] enough for 8.15 [hours] flying
possible additional useful load : 193 [kg]
operational weight fully loaded : 5889 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 5889 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 7.91 [kg/kW]
total power : 551.6 [kW] at 1950 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.2 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]
design flight time : 6.26 [hours]
design cycles : 152 sorties, design hours : 950 [hours]
operational wing loading : 396 [N/m^2]
wing stress (3 g) during operation : 170 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.05 ["]
max. angle of attack (stalling angle) : 9.66 ["]
angle of attack at max. speed : 3.71 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.02 [ ]
lift coefficient at max. speed : 0.45 [ ]
induced drag coefficient at max. speed : 0.0062 [ ]
drag coefficient at max. speed : 0.0866 [ ]
drag coefficient (zero lift) : 0.0804 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 91 [km/u]
landing speed at sea-level (OW without bombload): 109 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 109 [km/hr] at 1905 [m] (power:46 [%])
min. power speed (max range) : 109 [km/hr] at 1905 [m] (power:46 [%])
cruising speed : 126 [km/hr] op 1905 [m] (power:62 [%])
design speed prop : 133 [km/hr]
maximum speed : 140 [km/hr] op 610 [m] (power:90 [%])
Ground Crew manoeuvre Curtiss H16 Flying boat to cradle after first flight in Cork
climbing speed at sea-level (without bombload) : 279 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 455 [m]
lift/drag ratio : 10.12 [ ]
max. practical ceiling : 4200 [m] with flying weight :3885 [kg]
practical ceiling (operational weight): 3700 [m] with flying weight :4362 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2300 [m] with flying weight :5777 [kg]
published ceiling (3810 [m]
climb to 1500m (without bombload) : 6.22 [min]
max. dive speed : 329.2 [km/hr] at 1300 [m] height
load factor at max. angle turn 1.93 ["g"]
turn radius at 500m: 79 [m]
time needed for 360* turn 13.9 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 10.15 [hours] with 4 crew and 613 [kg] bombload and 100.0 [%] fuel
published endurance : 8.95 [hours] with 4 crew and possible useful (bomb) load : 748 [kg] and 88.1 [%] fuel
action radius : 973 [km] with 4 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 2811 [litre] fuel : 2317 [km]
useful load with action-radius 250km : 1616 [kg]
production : 203.58 [tonkm/hour]
oil and fuel consumption per tonkm : 0.59 [kg]
Literature :
Praktisch handbook vliegtuigen deel 1 page 243
Jane’s fighting aircraft WWI page 229
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/
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(c) B van der Zalm 23 November 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4