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"Je" (je ne suis que l'intermédiaire) recherche le maximum d'info sur le MS406.
La personne qui a besoin de ces renseignements a mis dans le fichier ci-joint toutes les infos qu'elle possède.
Si vous pouviez modifier ou completer ces infos, ça serait cool

Merci

PS: Il est anglophone et ne parle pas français, donc pas la peine de me donner des titres de livres français dans lesquels il pourrait chercher.

Chercher des infos sur le MS-406 sans parler Français...
Bon courage.

III/JG52-Freiherr V. Kaos a écrit :Chercher des infos sur le MS-406 sans parler Français...
Bon courage.

Yep, déjà que en français c'est pas la joie....

Quelle plaie ces unités impérial(ist)es! Une bonne âme pour convertir ça en SI? J'ai un peu de doc, mais.... pfffffffffff...

Cela dit, c'est vrai, il est fort difficile de trouver ce genre de trucs sans rendre soi-même visite aux archives... On a l'impression qu'il n'y a plus d'historien français qui s'intéresse à la technique depuis Danel et Cuny, et c'est bien dommange.

Si ca peut te d"panner tu as ce site http://gofree.indigo.ie/~janoty/euskadi/conv_val.htm

Je suis vraiment une bonne poire... je me suis tapé la traduction de ma doc. Tout n'y est pas, je dois vérifier avec d'autres sources... mais ça sera tout pour ce soir parce que là j'en ai marre :D
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From Aero-Journal n°6/7, 1973

Airframe
========

Wingspan: 10.62 m
Lenght: 8.17 m
Height tail down: 2.84 m
Height tail up: 1.84 m
Propeller ground clearance, tail down: 0.85 m
Propeller ground clearance, tail up: 0.54 m
Shock absorber course: 0.20 m

Wings
Dihedral angle: 12%
Chord @ root: 2.35 m
Chord @ wingtip: 1.23 m
Total area: 16 m2
Build-in incidence angle: 2°

Ailerons
max lenght: 1.87 m
max chord: 0.35 m
distance between aileron centre to aircraft axis: 3.88 m
(note: no data on throwout angles)

Fuselage
Height, largest frame: 1.65 m
Width, largest frame: 0.90 m
Frontal surface: 1.17 m2

Tail
Horizontal tailplane:
span: 3.50 m
Stabilizers area: 1.20 m2
Elevators area: 1.26 m2
Distance from elevator axis to main wing leading edge: 5.68 m
Vertical tailplane:
max height: 1.89 m
Stabilizer area: 0.61 m2
Rudder area: 0.77 m2
Distance from rudder axis to main wing leading edge: 5.86 m
(note: no data on throwout angles)

Powerplant
==========

Engine:
Type and make: Hispano-Suiza 12Y31
12-cylinders vee, liquid-cooled
Single speed, single stage supercharger
Carburator-fed
(note: no negative gee capability)
max power @ sea level: 760 metric hp @ 2000 rpm @ 880 mm Hg
max power @ altitude: 860 metric hp @ 2400 rpm (?) @ 880 mm Hg
time-limited take-off power @ sea level: 860 metric hp @ 2000 rpm @ 960 mm Hg
altitude of rated power: 3250 m (on testbed)
fuel type: 85 octane
propeller reductor ratio: 2/3
Propeller:
make and type: Chauviere series 351
diameter: 3.00 m
Max coarse pitch: 41.44 grad
Min fine pitch: 30.36 grad

Tanks
Fuel tanks:
Number: 2, metallic
(note: aux tank is on top, main tank is below cannon breech)
protection:
main: yes
auxiliary: no
(note: on other French planes of the same era, "protected tank" means tank is coated with "Superflexit" self-sealing covering

material. No data on what's on the MS.406 exactly, though)
Theoretical capability:
main: 325 l
auxiliary: 81l
total: 406 l
Practical capability:
main: 320 l
auxiliary: 80 l
total: 400 l
Oil tank
type: metallic, unprotected
Theoretical capability: 49 l
Practical capability: 38 l
(note: oil tank is fitted in nose below engine and in front of radiator)

Flight characteristics
======================

Max speed @ 5000 m @ 2400 RPM @ 880 mm Hg IMAP: 486 km/h TAS (380 km/h IAS)
Min speed @ 1000 m @ 1120 RPM, flaps up, gear up, radiator up: 160 km/h TAS (150 km/h IAS)
Min speed @ 1000 m @ 1230 RPM, flaps down, gear down, radiator down: 142 km/h TAS (135 km/h IAS)

Manoeuvres @ 2000 m:

Dive with reduced throttle: 585 km/h IAS, 71 m/s descent rate, 24° nose down attitude
Immelman zoom climb:
starting @ 380 km/h IAS: climbs by 550 m in 25 s.
starting @ 300 km/h IAS: climbs by 350 m in 17 s.
Acceleration: from min to max level speed in 65 s.
from max to min in 50 s.

Turn capability (360° turns):
Tight full level turn @ full power:
starting speed: 320 km/h IAS
time: 15.2 s
4.6 g
radius: 265 m

Tight full turn @ reduced power:
starting speed: 180 km/h IAS
time: 4 s
2.6 g
radius: 142 m
rate of descent: 20 m/s


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From untitled documents preserved at the Musee de l'air
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Weight statements, day fighter mission:

powerplant: 866 kg
tanks (empty): 53 kg
airframe: 831 kg
Fixed equipment: 145 kg
total empty weight: 1895 kg

variable equipment: 122 kg
(note: guns and ammo probably)
Fuel (400 l): 320 kg
Oil: 35 kg
Crew: 88 kg

Total gross take-off weight: 2460 kg

First set of performance data
take-off weight: 2435 kg (other conditions unknown, probably MS.405-01 prototype?)
alt (m) time to alt max level speed (km/h)
=================================================
500 38 s 410
1000 1 m 14 s 417
2000 2 m 56 s
3000 4 m 27 s 452
4000 5 m 59 s 471
5200 7 m 36 s 486
6000 9 m 37 s 470
7000 12 m 453
8000 15 m 46 s 435

Second set of performance data
conditions unknown
alt (m) time to alt max level speed (km/h)
=================================================
2000 2 m 32 s 452
4000 5 m 16 s 483
4500 6 m 16 s 490
6000 9 m 03 s 476
8000 14 m 52 s 440

Max practical ceiling: 10000m
Take-off run, clearing a 8 m-high obstacle: 270 m
Landing run, beyond a 8 m-high obstacle: 340 m

Endurance:
@ full power @ 4000 m: 1 h 30 m (720 km)
@ cruise power (320 km/h, 33% power) @ 4000 m: 3 h 30 m (1100 km)

merci Pachy