Maximální vzletová hmotnost: Maximum Take-off Weight:
7500 kg
16535 lb
Rozpětí: Wingspan:
15,700 m
51ft 6,11in
Délka: Length:
11,800 m
38ft 8,56in
Výška: Height:
4,280 m
14ft 0,5in
Plocha křídla: Wing Area:
33,06 m2
355.85 ft2
Plošné zatížení: Wing Loading:
196,612 kg/m2
40.27 lb/ft2
Pohon: Propulsion:
Kategorie: Category:
pístový
piston
Počet motorů: Number of Engines:
2
Typ: Type:
Gnome-Rhône 14N-21 vzduchem chlazený dvouhvězdicový čtrnáctiválec o vzletovým výkonu 834,8 kW (1 135 k) Vrtule třílistá stavitelná Gnome-Rhône
Gnome-Rhône 14N-21 fourteen-cylinder two-row air-cooled engine rated at 1,119 hp for take-off, driving a three-bladed variable-pitch propeller Gnome-Rhône
Objem palivových nádrží: Fuel Tank Capacity:
?
?
Výkony: Performance:
Maximální rychlost: Maximum Speed:
580 km/h v 6500 m
360.4 mph in 21325 ft
Cestovní rychlost: Cruise Speed:
500 km/h v 5000 m
310.7 mph in 16404 ft
Rychlost stoupání: Climb Rate:
16,0 m/s
3149.6 ft/min
Čas výstupu na výšku: Time to Climb to:
? min do ? m
? min to ? ft
Operační dostup: Service Ceiling:
8900 m
29199 ft
Dolet: Range:
1300 km
807.8 mi
Maximální dolet: Maximum Range:
? km
? mi
Výzbroj: Armament:
nebyla instalována, ale počítalo se s 4x pevný kanón HS 404 ráže 20 mm (po 60 nábojích) 1x pohyblivý kanón HS 404 ráže 20 mm ve hřbetním střelišti.
proposed: Four fixed forward-firing 0.79 inch HS 404 cannon, 60 rpg cannons in nose and one flexible rearward-firing 0.79 inch HS 404 cannon in a dorsal position.
Uživatelské státy: User States:
-
-
Poznámka: Note:
-
-
Zdroje: Sources:
Dominique Breffort & André Jouineau, L'Aviation française de 1939 á 1942. Tome 2., Paris, Histoire et Collections, 2005. ISBN 2-915239-48-7. William Green, Gordon Swanborough, Encyklopedie stíhacích letounů, Svojtka & Co., Praha 2002, ISBN 80-7237-341-2. Václav Němeček, SNCASE SE-100, Letectví + Kosmonautika, č.18/1968. www.aviafrance.com http://www.airwar.ru/enc/fww2/se100.html www.sas1946.com
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SNCASE SUD-EST SE.100
Origin: In 1936, the French Air Force announced a competition for a new twin-engine multi-purpose (in the primary role - heavy fighter) aircraft, which should in the first phase replace heavy fighters Potez 630/ 631 and subsequently other types (battle, light bomber) aircraft. For example, the French State Consortium of Airlines with a modified version of the Hanriot H-220, Caudron with the project C.900 entered the competition, but also a design team from Lioré-et-Olivier with the project LeO-50. Most of the submitted proposals did not bring any revolutionary new ideas or constructions. However, the LeO-50 project attracted both the selection committee and the Air Force Command. Designers Pierre-Ernest Mercier and Jacques Lecarme from the Lioré-et-Olivier design office offered an unconventional aircraft, promising high performance and good performance. In the initial phase, the project was designated LeO-50, but when in 1937 the whole company passed under the common state roof SNCASE, the designation of the new aircraft was changed to SNCASE SE-100. The first prototype began to be slowly built in 1936 as the LeO-50. After the transition to the new management, however, both the designation and the pace of work changed, which increased significantly.
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Reklama
Prototypes:
The first flight of the prototype redesignated the SE-100.01 took place on March 29, 1938. As could be expected for the new aircraft, it did not go without problems. The control of the aircraft was described as unstable, with rapid transitions to crisis modes and engine power was assessed as insufficient. There were also two emergency landings in a few flights. Overall, however, the type was rated as very interesting. It was decided to continue development and the machine was sent to the manufacturer for modifications. The design changes mainly concerned the steering system, increasing the stabilization areas and increasing the effects of the brakes. During these modifications, the volume of fuel tanks was also increased and more powerful propulsion units were installed. The modified aircraft was handed over for military tests for approximately 10 hours after the raid. These did not begin until 1940. During the tests, the maximum speed of 579 km/h was measured and the control of the aircraft was assessed as satisfactory. During the spring months, however, an accident occurred during the landing maneuver, during which the prototype was destroyed. The entire crew of the plane perished in its wreckage. At that time, however, just before the completion of the second prototype was called SE-100.02. This was to be a model for a three-seater variant of this machine. All known ailments that revealed the SE-100.01 tests have already been eliminated. This machine has also already received an all-metal wing. Furthermore, the fuel supply was increased and stronger armaments were installed. The expected performance of the second prototype and the experience with the operation of the first prototype so impressed the representatives of the Air Force that immediately began negotiations on the start of production of the SE-100 aircraft.
However, the invasion of France eventually stopped the whole process.
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Construction:
Prototype SE-100.01 The fuselage of the first prototype was welded from duralumin profiles. It was covered with canvas and only in exposed and more stressed places it was covered with duralumin panels. The bow of the fuselage was without glazing, designed as a solid structural unit designed to install weapons. The crew cabins were completely glazed. The rich glazing allowed a really good view. The wings were wooden with a canvas cover. There were flaps along the entire length of the trailing edge. The end arches of the wings were oval and movable. The drive units were attached to the leading edge. The GTC with double SOPs had a relatively large margin. The purpose was to provide the rear gunner with a large firing angle. The lower part of both SOPs were structurally reinforced, because the rear chassis legs found their place there. In the first phase, the aircraft was equipped with two fourteen-cylinder star Gnome-Rhone 14M-8/9 with an output of 800 horsepower. During the first flight, however, the aircraft already had a stronger Gnome-Rhone 14N-0/1 of 763 kW (1038 hp). After the modernization, more powerful Gnome-Rhone 14N-20/21 with an output of 772 kW (1050 hp) were installed. The chassis would be designed as a three-point. Interestingly, however, the front landing gear leg was inserted into the bow of the fuselage under the armament and the other two retractable legs were located in the lower parts of both SOPs, into which they retracted. The armament was placed in the bow (offensive) and in the dorsal range (defensive). A defensive 20mm cannon was to be used for defense, and in the bow was calculated with a different composition of armament. This should be guided by the nature of the tasks assigned to the given version of the aircraft as well as the type and endurance of the targets. It was planned to install 20 mm cannons (up to six pieces), 7.62 or 12.7 mm machine guns (up to eight pieces) or a combination of cannons and machine guns.
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Prototype SE-100.02
The fuselage of the second prototype was also welded from duralumin profiles. It was also partly covered with canvas, but it was covered with duralumin panels in several places. The bow of the fuselage was without glazing, designed as a solid structural unit designed to install weapons. The crew cabins were completely glazed. The rich glazing allowed a really good view. The wings were all-metal with a larger bearing area. There were flaps along the entire length of the trailing edge. The end arches of the wings were oval and movable. The drive units were attached to the leading edge. The GTC with double SOPs had a relatively large margin. The purpose was to provide the rear gunner with a large firing angle. The lower part of both SOPs were structurally reinforced, because the rear chassis legs found their place there. The No. 2 aircraft was first equipped with two Gnome-Rhone 14N-24/25 engines of 809 kW (1100 hp) and later more powerful Gnome-Rhone 14N-48/49 with an output of 838 kW (1140 hp). The chassis would be designed as a three-point and was structurally arranged as in the prototype No. 1. The armament was placed in the bow (offensive) and in the dorsal range (defensive). A defensive 20 mm cannon was to be used for defense, and four fixed cannons of the same caliber were planned in the bow.
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