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weight and performance calculations for the Fokker F-14
Fokker F-14
role : medium weight passenger aircraft
importance : **
first flight : operational : December 1929
first flight : December 1929 operational : only small number built
country : United States of America
design :
production : 14 aircraft at Teterboro apt. (20 Y1C-14 for the US Army)
general information :
Combi aircraft > mail & passenger aircraft. Open cockpit behind the wing. The mail service pilots were used to this configuration. It had a parasol wing mounted on struts to give the pilot a better forward view.
users : Western Canada Airways (6), Western Air Express (4)
registrations : CF-AIG
crew : 1 passengers : 8
engine : 1 Pratt & Whitney R-1690 Hornet air-cooled 9 -cylinder radial engine 525 [hp]
(391.5 KW) without supercharger
dimensions :
wingspan : 18.11 [m], length : 13.25 [m], height : 3.76[m]
wing area : 51.19 [m^2]
weights :
max.take-off weight : 3266 [kg]
empty weight operational : 1971 [kg] useful load : 900 [kg]
performance :
maximum speed :220 [km/hr] at sea-level
cruise speed :198 [km/u] op 100 [m]
service ceiling : 4420 [m]
range : 1280 [km]
description :
parasol wing with fixed landing gear and tail strut
two spar tapered wing
engine, fuel and useful load in or attached to fuselage, landing gear attached to the
wing
F-14 with Townend ring for better aerodynamics.
airscrew :
fixed pitch 2 -bladed metal Curtiss Reed tractor airscrew with max. efficiency :0.71 [ ]
estimated diameter airscrew 3.20 [m]
power loading prop : 122.34 [KW/m]
prop efficiency ratio: 6.84 [1/s]
angle of attack prop : 14.36 [ ]
reduction : 1.00 [ ]
airscrew revs : 1900 [r.p.m.]
pitch at Max speed 1.93 [m]
blade-tip speed at Vmax and max revs. : 324 [m/s]
calculation : *1* (dimensions)
measured wing chord : 3.02 [m] at 50% span
mean wing chord : 2.83 [m]
calculated average wing chord tapered wing with rounded tips: 2.84 [m]
wing aspect ratio : 6.41 []
seize (span*length*height) : 902 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.3 [kg/hr]
fuel consumption(cruise speed) : 95.0 [kg/hr] (129.6 [litre/hr]) at 66 [%] power
distance flown for 1 kg fuel : 2.08 [km/kg] at 2210 [m] height, sfc : 366.4 [kg/kwh]
estimated total fuel capacity : 951 [litre] (697 [kg])
calculation : *3* (weight)
weight engine(s) dry : 362.0 [kg] = 0.92 [kg/KW]
weight 63.9 litre oil tank : 5.43 [kg]
oil tank filled with 2.9 litre oil : 2.6 [kg]
oil in engine 2.2 litre oil : 2.0 [kg]
fuel in engine 2.7 litre fuel : 1.96 [kg]
weight 55.1 litre gravity patrol tank(s) : 8.3 [kg]
weight inertia starter : 9.6 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 47.7 [kg]
total weight propulsion system : 434 [kg](13.3 [%])
***************************************************************
Measured wing chord at root : 3.69 [m], at 50% span : 3.02 [m]
fuselage skeleton (steel tubes) : 6.77 [cm]): 478 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 4.0 rows
weight toilet : 5 [kg]
weight 1 fire extinguisher : 3 [kg]
weight 8.0 windows : 7.20 [kg]
passenger cabin width : 1.35 [m] cabin length : 3.48 [m] cabin height : 1.90 [m]
weight cabin furbishing : 18.65 [kg]
weight cabin floor : 30.12 [kg]
bracing : 44.7 [kg]
fuselage covering ( 33.2 [m2] doped linen fabric) : 10.2 [kg]
weight radio navigation equipment : 7.0 [kg]
weight instruments. : 4.0 [kg]
weight lighting : 2.0 [kg]
weight controls : 6.9 [kg]
weight seats : 45.0 [kg]
weight 896 [litre] main fuel tank empty : 71.7 [kg]
weight air conditioning : 12 [kg]
weight engine mounts & firewalls : 20 [kg]
total weight fuselage : 765 [kg](23.4 [%])
***************************************************************
weight 2.4 mm plywood wing covering : 79 [kg]
total weight ribs (63 ribs) : 194 [kg]
load on front upper spar (clmax) per running metre : 1420.5 [N]
load on rear upper spar (vmax) per running metre : 480.3 [N]
total weight 4 spars : 225 [kg]
weight wings : 498 [kg]
weight wing/square meter : 9.72 [kg]
cantilever wing without bracing cables
weight fin & rudder (3.8 [m2]) : 37.6 [kg]
weight stabilizer & elevator (5.8 [m2]): 56.4 [kg]
total weight wing surfaces & bracing : 592 [kg] (18.1 [%])
*******************************************************************
wheel pressure : 1633.0 [kg]
weight 2 wheels (980 [mm] by 196 [mm]) : 80.2 [kg]
weight tailskid : 8.3 [kg]
weight undercarriage with axle 80.1 [kg]
total weight landing gear : 168.6 [kg] (5.2 [%]
*******************************************************************
********************************************************************
calculated empty weight : 1959 [kg](60.0 [%])
weight oil for 7.8 hours flying : 48.6 [kg]
calculated operational weight empty : 2008 [kg] (61.5 [%])
published operational weight empty : 1971 [kg] (60.3 [%])
***o***
"
weight crew : 81 [kg]
weight fuel for 2.0 hours flying : 190 [kg]
********************************************************************
operational weight empty: 2279 [kg](69.8 [%])
weight 8 passengers : 616 [kg]
weight luggage & freight : 284 [kg]
operational weight loaded: 3179 [kg](97.3 [%])
fuel reserve : 87.2 [kg] enough for 0.92 [hours] flying
operational weight fully loaded : 3266 [kg] with fuel tank filled for 40 [%]
published maximum take-off weight : 3266 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 8.34 [kg/kW]
power loading (operational without useful load) : 5.82 [kg/kW]
total power : 391.5 [kW] at 1900 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.4 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.2 [g]
design flight time : 4.53 [hours]
design cycles : 4515 sorties, design hours : 20430 [hours]
operational wing loading : 437 [N/m^2]
wing stress (3 g) during operation : 135 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.24 ["]
max. angle of attack (stalling angle) : 12.88 ["]
angle of attack at max. speed : 1.15 ["]
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 : 0.19 [ ]
induced drag coefficient at max. speed : 0.0025 [ ]
drag coefficient at max. speed : 0.0387 [ ]
drag coefficient (zero lift) : 0.0362 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 3171 [kg]): 106 [km/u]
landing speed at sea-level: 125 [km/hr]
min. drag speed (max endurance) : 147 [km/hr] at 2210 [m](power :45 [%])
Y1C-14 in service with the US Army air service. Pratt & Whitney R-1750-3 Hornet B 575 hp engine
min. power speed (max range) : 147 [km/hr] at 2210 [m] (power:45 [%])
max. rate of climb speed : 129.9 [km/hr] at sea-level
cruising speed : 198 [km/hr] op 2210 [m] (power:72 [%])
design speed prop : 209 [km/hr]
maximum speed : 220 [km/hr] op 100 [m] (power:105 [%])
climbing speed at sea-level : 419 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 129.4 [km/u]
static prop wash : 171 [km/u]
take-off distance at sea-level : 203 [m]
lift/drag ratio : 10.21 [ ]
climb to 1000m with max payload : 5.09 [min]
climb to 2000m with max payload : 12.41 [min]
climb to 3000m with max payload : 22.58 [min]
practical ceiling (operational weight 2279 [kg] ) : 6268 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:3218 [kg] ) : 4358 [m]
max. dive speed : 475.5 [km/hr] at 3358 [m] height
turning speed at CLmax : 145.5 [km/u] at 50 [m] height
turn radius at 50m: 69 [m]
time needed for 360* turn 10.8 [seconds] at 50m
load factor at max. angle turn 2.60 ["g"]
calculation *10* (action radius & endurance)
published range : 1280 [km] with 1 crew and 563.0 [kg] useful load and 88.1 [%] fuel
dit bereik is niet mogelijk met alle pax > nakijken, evt bereik verlagen
range : 578 [km] with 1 crew and 900.0 [kg] useful load and 39.8 [%] fuel
range : 1003 [km] with 8.0 passengers with each 10 [kg] luggage and 69.0 [%] fuel
Available Seat Kilometers (ASK) : 8023 [paskm]
max range theoretically with additional fuel tanks total 1606.1 [litre] fuel : 2453 [km]
useful load with range 500km : 937 [kg]
useful load with range 500km : 8 passengers
production (useful load): 185.59 [tonkm/hour]
production (passengers): 1584.00 [paskm/hour]
oil and fuel consumption per tonkm : 0.55 [kg]
oil and fuel consumption per paskm : 0.06 [kg]
fuel cost per paskm : 0.06 [eur]
crew cost per paskm : 0.09 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 175 [hr]
writing off per paskm : 0.07 [eur]
insurance per paskm : 0.0487 [eur]
maintenance cost per paskm : 0.1930 [eur]
direct operating cost per paskm : 0.47 [eur]
Literature :
Fokker verkeersvliegtuigen page 128-131
Piston-engined airliners page 18,19
Fokker verkeersvliegtuigen 1920-1940 page 76,78
Fokkers “roaring twenties” page 47
Alles over de Fokker Friendship page 61
Fokker – bouwer aan de wereldluchtvaart page 81
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 10 May 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4