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weight and performance calculations for the Pfalz E.I
Pfalz E.I
role : fighter
importance : ****
first flight : operational : October 1915
country : Germany
design : license built copy of Morane Saulnier type H slightly modified
production : 60 aircraft, Speyer am Rhein
general information
Before WWI, the Pfalz flugzeug-werke, founded in July 1913 and led by the brothers Eversbusch (Alfred, Walter and Ernst) acquired the rights to build the Morane Saulnier L and H under license. The E.I was actually a recreated Morane Saulnier H equipped with a synchronized machine gun. The E.II had a 100 hp rotation engine.
About as many of them were built as the Fokker E.I. April 1916 flew the most at the front: 27 pieces ! The Pfalz could only be distinguished from the Fokker E.I on the keel surface and the Allies almost always saw it for a Fokker monoplane.
It had a wooden airframe contrarily to the Fokker E.I which had a welded steel-tube fuselage.
users : Luftwaffe
crew : 1
armament : 1 synchronized 7.92 [mm] (0.312 in) Spandau LMG 08/15 machine-gun
engine : 1 Oberursel U.O air-cooled 7 -cylinder atmospheric inlet-valve rotary engine 80 [hp](59.7 KW)
dimensions :
wingspan : 9.25 [m], length : 6.3 [m], height : 2.55[m]
wing area : 14.0 [m^2]
weights :
max.take-off weight : 535 [kg]
empty weight operational : 345 [kg] bombload : 0 [kg]
performance :
maximum speed : 140 [km/hr] at sea-level
climbing speed : 267 [m/min]
service ceiling : 3500 [m]
endurance : 1.5 [hours]
estimated action radius : 94 [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
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.63 [ ]
estimated diameter airscrew 2.00 [m]
angle of attack prop : 21.61 [ ]
reduction : 1.00 [ ]
airscrew revs : 1250 [r.p.m.]
pitch at Max speed 1.87 [m]
blade-tip speed at Vmax and max revs. : 137 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.51 [m]
calculated wing chord (rounded tips): 1.92 [m]
wing aspect ratio : 6.11 []
gap : 0.00 [m]
gap/chord : 0.00 [ ]
seize (span*length*height) : 149 [m^3]
The Fokker is recognizable by the round keel surface. Also, the landing gear is different but that is not visible in this photo.
calculation : *2* (fuel consumption)
oil consumption : 6.6 [kg/hr]
fuel consumption(cruise speed) : 18.3 [kg/hr] (24.9 [litre/hr]) at 69 [%] power
distance flown for 1 kg fuel : 6.90 [km/kg]
estimated total fuel capacity : 42 [litre] (31 [kg])
calculation : *3* (weight)
weight engine(s) dry : 118.1 [kg] = 1.98 [kg/KW]
weight 15 litre oil tank : 1.8 [kg]
oil tank filled with 0.4 litre oil : 0.4 [kg]
oil in engine 0 litre oil : 0.3 [kg]
fuel in engine 0 litre fuel : 0.3 [kg]
weight 11 litre gravity patrol tank(s) : 1.0 [kg]
weight cowling 2.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 13.7 [kg]
total weight propulsion system : 136 [kg](25.5 [%])
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fuselage skeleton (wood gauge : 5.05 [cm]): 41 [kg]
bracing : 1.8 [kg]
fuselage covering ( 7.5 [m2] doped linen fabric) : 2.4 [kg]
weight controls + indicators: 5.4 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight 32 [litre] main fuel tank empty : 3.1 [kg]
weight engine mounts & firewalls : 3 [kg]
total weight fuselage : 65 [kg](12.1 [%])
***************************************************************
weight wing covering (doped linen fabric) : 9 [kg]
total weight ribs (29 ribs) : 32 [kg]
load on front upper spar (clmax) per running metre : 536.3 [N]
load on rear upper spar (vmax) per running metre : 164.4 [N]
total weight 4 spars : 26 [kg]
weight wings : 67 [kg]
weight wing/square meter : 4.79 [kg]
Fischinger Erwin 16.12.1892 Eßlingen ledig Student Leutnant der Reserve Kampfgeschwader 2 Obere Heeresleitung Kampfstaffel 7 verunglückt 09.04.1916 Flugplatz Freskaty, gestorben am Abend nach Einlieferung in das Festungslazarett Lehrerseminar Montigny bei Metz, FFA21
weight cables (37 [m]) : 8.1 [kg] (= 219 [gram] per metre)
diameter cable : 6.0 [mm]
weight fin & rudder (1.0 [m2]) : 4.9 [kg]
weight stabilizer & elevator (1.6 [m2]): 7.6 [kg]
total weight wing surfaces & bracing : 88 [kg] (16.4 [%])
*******************************************************************
weight machine-gun(s) : 17.0 [kg]
weight ammunition magazine(s) :2.3 [kg]
weight Fokker Stangensteuerung synchronization gear : 1.0 [kg]
weight armament : 20 [kg]
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wheel pressure : 267.5 [kg]
weight 2 wheels (670 [mm] by 80 [mm]) : 12.6 [kg]
weight tailskid : 1.5 [kg]
weight undercarriage with axle 17.3 [kg]
total weight landing gear : 31.3 [kg] (5.9 [%]
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calculated empty weight : 340 [kg](63.6 [%])
weight oil for 1.8 hours flying : 11.8 [kg]
weight ammunition (500 rounds) : 14.1 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 368 [kg] (68.7 [%])
published operational weight empty : 345 [kg] (64.5 [%])
---o---
"
weight crew : 81 [kg]
weight fuel for 1.5 hours flying : 27 [kg]
********************************************************************
operational weight : 476 [kg](89.0 [%])
estimated bomb load : 25 [kg]
operational weight bombing mission : 501 [kg]
fuel reserve : 4 [kg] enough for 0.20 [hours] flying
possible additional useful load : 30 [kg]
operational weight fully loaded : 535 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 535 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 7.98 [kg/kW]
total power : 59.7 [kW] at 1250 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 1.8 [g] at 1000 [m]
limit load : 4.5 [g] ultimate load : 6.8 [g] load factor : 2.4 [g]
design flight time : 1.20 [hours]
design cycles : 458 sorties, design hours : 550 [hours]
operational wing loading : 333 [N/m^2]
wing stress (3 g) during operation : 209 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.26 ["]
max. angle of attack (stalling angle) : 12.99 ["]
angle of attack at max. speed : 3.31 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
lift coefficient at max. speed : 0.36 [ ]
induced drag coefficient at max. speed : 0.0092 [ ]
drag coefficient at max. speed : 0.0740 [ ]
drag coefficient (zero lift) : 0.0648 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 79 [km/u]
landing speed at sea-level (OW without bombload): 95 [km/hr]
min. drag speed (max endurance) : 95 [km/hr] at 1750 [m](power :48 [%])
min. power speed (max range) : 109 [km/hr] at 1750 [m] (power:55 [%])
max. rate of climb speed : 88.0 [km/hr] at sea-level
cruising speed : 126 [km/hr] op 1750 [m] (power:70 [%])
design speed prop : 136 [km/hr]
maximum speed : 140 [km/hr] op 100 [m] (power:99 [%])
climbing speed at sea-level (without bombload) : 225 [m/min]
calculation : *9* (regarding various performances)
static prop wash : 17 [m/s]
take-off distance at sea-level : 281 [m]
max. practical ceiling : 4050 [m] with flying weight :442 [kg]
practical ceiling (operational weight) : 3650 [m] with flying weight :476 [kg] line 3385
practical ceiling fully loaded (mtow- 1 hour fuel) : 3150 [m] with flying weight :517 [kg]
published ceiling (3500 [m]
climb to 1500m (operational weight without bombload) : 7.72 [min]
climb to 3000m (operational weight without bombload) : 21.28 [min]
max. dive speed : 320.9 [km/hr] at 2150 [m] height
load factor at max. angle turn 1.77 ["g"]
turn radius at 500m: 62 [m]
time needed for 360* turn 13.1 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 1.70 [hours] with 1 crew and 55 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 1.50 [hours] with 1 crew and possible useful (bomb) load : 59 [kg] and 88.1 [%] fuel
action radius : 229 [km] with 1 crew and 20[kg] photo camera or bombload
max range theoretically with additional fuel tanks for total 139 [litre] fuel : 702 [km]
useful load with action-radius 250km : 29 [kg]
production : 3.69 [tonkm/hour]
oil and fuel consumption per tonkm : 6.72 [kg]
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Literature :
Warplanes WWI page 48
German aircraft of the first world war page 183
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 12 July 2020 contact : info.aircraftinvestigation@gmail.com python 3.7.4