S.E.5 with high windscreen to protect the pilot for the wind when operating the Lewis gun on the topplane. It was soon replaced by a smaller one.
RAF S.E.5
role : fighter
first flight : operational : April 1917
country : United-Kingdom
design :
production : S.E.5 59 aircraft
general information :
The famous ace Albert Ball did not like the S.E.5 in the beginning, he preferred his
loved agile Nieuport 17. He made changes to the S.E.5 by replacing the big
“Greenhouse” windscreen by a small windscreen. Also the elevated seat was lowered. It
gave the S.E.5 just the extra speed to fight the Albatros fighters. On 22 April 1917 56
sq. made its first patrol over the front in France. In the summer of 1917 56sq. was
moved back to the UK to defend London against the Gotha G.IV raids.
users : RFC
crew : 1
armament : 1 synchronized 7.70 [mm] (0.303 in) Vickers machine-gun
and 1 fixed 7.70 [mm] (0.303 in) Lewis machine-gun on top plane
engine : 1 Hispano Suiza 8Aa liquid-cooled 8 -cylinder V-engine 150 [hp](110.3 KW)
dimensions :
wingspan : 8.12 [m], length : 6.38 [m], height : 2.87[m]
wing area : 22.67 [m^2]
weights :
max.take-off weight : 877 [kg]
empty weight operational (estimation): 605.0 [kg] bombload : 20 [kg]
performance :
maximum speed : 183 [km/u] op 3048 [m]
service ceiling : 5182 [m]
endurance : 2.3 [hours]
estimated action radius : 189 [km]
description :
1-bay biplane with fixed landing gear and tail strut
two spar upper and lower wing
engines, landing gear, fuel and bombs in or attached to the fuselage
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.67 [ ]
estimated diameter airscrew 2.38 [m]
angle of attack prop : 19.93 [ ]
reduction : 1.00 [ ]
airscrew revs : 1500 [r.p.m.]
pitch at Max speed 2.03 [m]
blade-tip speed at Vmax and max revs. : 194 [m/s]
calculation : *1* (dimensions)
mean wing chord : 1.40 [m]
calculated wing chord (rounded tips): 1.60 [m]
wing aspect ratio : 5.82 []
gap : 1.38 [m]
gap/chord : 0.99 [ ]
seize (span*length*height) : 149 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 1.7 [kg/hr]
fuel consumption(cruise speed) : 24.0 [kg/hr] (32.7 [litre/hr]) at 59 [%] power
distance flown for 1 kg fuel : 6.87 [km/kg]
estimated total fuel capacity : 85 [litre] (63 [kg])
calculation : *3* (weight)
weight engine(s) dry : 215.0 [kg] = 1.95 [kg/KW]
weight 8 litre oil tank : 0.7 [kg]
oil tank filled with 0.8 litre oil : 0.7 [kg]
oil in engine 6 litre oil : 5.5 [kg]
fuel in engine 1 litre fuel : 0.6 [kg]
weight 14 litre gravity patrol tank(s) : 2.1 [kg]
weight radiator : 15.8 [kg]
weight exhaust pipes & fuel lines 12.7 [kg]
weight cowling 4.4 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 19.0 [kg]
total weight propulsion system : 276 [kg](31.5 [%])
***************************************************************
fuselage skeleton (wood gauge : 6.01 [cm]): 59 [kg]
bracing : 2.7 [kg]
fuselage covering ( 7.7 [m2] doped linen fabric) : 2.5 [kg]
weight controls + indicators: 5.3 [kg]
weight seats : 3.0 [kg]
weight other details, lighting set, etc. : 5.1 [kg]
weight bomb storage : 1.4 [kg]
weight 71 [litre] main fuel tank empty : 5.7 [kg]
weight engine mounts & firewalls : 6 [kg]
total weight fuselage : 90 [kg](10.3 [%])
***************************************************************
weight wing covering (doped linen fabric) : 15 [kg]
total weight ribs (51 ribs) : 52 [kg]
load on front upper spar (clmax) per running metre : 878.4 [N]
load on rear upper spar (vmax) per running metre : 311.2 [N]
total weight 8 spars : 33 [kg]
weight wings : 100 [kg]
weight wing/square meter : 4.40 [kg]
weight 4 interplane struts & cabane : 8.7 [kg]
weight cables (41 [m]) : 2.2 [kg] (= 52 [gram] per metre)
diameter cable : 2.9 [mm]
weight fin & rudder (0.8 [m2]) : 3.5 [kg]
weight stabilizer & elevator (2.6 [m2]): 11.4 [kg]
total weight wing surfaces & bracing : 126 [kg] (14.3 [%])
*******************************************************************
weight machine-gun(s) : 28.6 [kg]
Foster quadrant mounting and Bowden cable : 1.5 [kg]
weight ammunition magazine(s) :1.8 [kg]
weight synchronizing system : 1.0 [kg]
weight armament : 33 [kg]
********************************************************************
wheel pressure : 438.5 [kg]
weight 2 wheels (710 [mm] by 79 [mm]) : 21.4 [kg]
weight tailskid : 2.1 [kg]
weight undercarriage with axle 20.9 [kg]
total weight landing gear : 44.5 [kg] (5.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 569 [kg](64.9 [%])
weight oil for 2.8 hours flying : 4.6 [kg]
weight cooling fluids : 23.8 [kg]
weight 5 drums empty : 1.0 [kg]
weight ammunition (635 rounds) : 22.6 [kg]
weight Very pistol with cartridges : 3.6 [kg]
*******************************************************************
calculated operational weight empty : 623 [kg] (71.1 [%])
estimated operational weight empty : 605 [kg] (69.0 [%])
_____________
| o |
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"
weight crew : 81 [kg]
weight fuel for 1.5 hours flying : 36 [kg]
********************************************************************
operational weight : 740 [kg](84.4 [%])
bomb load : 20 [kg]
operational weight bombing mission : 760 [kg]
fuel reserve : 27 [kg] enough for 1.11 [hours] flying
possible additional useful load : 90 [kg]
operational weight fully loaded : 877 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 877 [kg] (100.0 [%])
||
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calculation : * 4 * (engine power)
power loading (operational without bombload) : 6.71 [kg/kW]
total power : 110.3 [kW] at 1500 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.2 [g] at 1000 [m]
limit load : 4.5 [g] ultimate load : 6.8 [g] load factor : 2.1 [g]
design flight time : 1.84 [hours]
design cycles : 277 sorties, design hours : 510 [hours]
operational wing loading : 320 [N/m^2]
wing stress (3 g) during operation : 218 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.53 ["]
max.angle of attack (stalling angle) : 12.85 ["]
angle of attack at max.speed : 1.97 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.12 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
lift coefficient at max.speed : 0.27 [ ]
induced drag coefficient at max.speed : 0.0073 [ ]
drag coefficient at max.speed : 0.0359 [ ]
drag coefficient (zero lift) : 0.0286 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 78 [km/u]
landing speed at sea-level (OW without bombload): 93 [km/hr]
min.drag speed (max endurance) : 130 [km/hr] at 3048 [m](power :40 [%])
min. power speed (max range) : 135 [km/hr] at 3048 [m] (power:42 [%])
max.rate of climb speed : 119.5 [km/hr] at sea-level
cruising speed : 165 [km/hr] op 3048 [m] (power:53 [%])
design speed prop : 178 [km/hr]
maximum speed : 183 [km/hr] op 3048 [m] (power:66 [%])
climbing speed at sea-level (without bombload) : 332 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 203 [m]
lift/drag ratio : 9.48 [ ]
max. practical ceiling : 5550 [m] with flying weight :690 [kg]
practical ceiling (operational weight): 5125 [m] with flying weight :740 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 4250 [m] with flying weight :853 [kg]
published ceiling (5182 [m]
climb to 1500m (without bombload) : 5.05 [min]
climb to 3000m (without bombload) : 12.42 [min]
max.dive speed : 444.5 [km/hr] at 3250 [m] height
load factor at max.angle turn 1.97 ["g"]
turn radius at 500m: 58 [m]
time needed for 360* turn 11.7 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 2.61 [hours] with 1 crew and 110 [kg] useful (bomb)load and 100.0 [%] fuel
published endurance : 2.30 [hours] with 1 crew and possible useful (bomb) load : 117 [kg] and 88.1 [%] fuel
action radius : 524 [km] with 1 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 271 [litre] fuel : 1366 [km]
useful load with action-radius 250km : 126 [kg]
production : 20.75 [tonkm/hour]
oil and fuel consumption per tonkm : 1.23 [kg]
_
I_°==/
°
Literature :
Praktisch handboek vliegtuigen deel 1 page 193
Fighters 1914-19 page 119
Bloody April page 156,157,158
They fought fort he sky page 161,180
De Groten van het luchtruim page 44,45
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.
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(c) B van der Zalm 04 January 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.2(32-bit)