Arsenal constructed two prototypes of the VG-90 and a first flight was recorded on September 27th, 1949. The second prototype differed in its armament fit - 2 x 20mm cannons, 2 x 7.7mm machine guns, an internal 36-shot rocket pack (RAC 50 rockets) and underwing launch rails for additional rockets (either 16 x T10 rockets or 80 x RAC 50 rockets). This model made its maiden flight during June of 1951.
Flight testing of the VG-90 was fraught with issues and both models were eventually lost in separate crashes - each claiming the life of its respective test pilot. On May 25th, 1950, one of the undercarriage panels became loose and hit the tail causing a loss of control and an inevitable crash. On February 21st, 1952, violent flutter was blamed for the tail section ripping off and sending the crippled aircraft spiraling to earth. Despite the aircraft carrying an ejection seat for its pilot, this system failed which ensured a loss of life. A third prototype had been planned that would have carried a SNECMA Atar 01F series turbojet engine of 8,818 lb thrust but due to the issues encountered with the flight testing of the earlier prototypes, this variant was not pursued into a physical form.
The program was eventually terminated and none of the three offered designs from the three competing companies were adopted for service in the French Navy.
As completed, the VG-90 sported a length of 13.4 meters, a wingspan of 12.6 meters and a height of 3.5 meters. Empty weight was 11,250 lb against a Maximum Take-Off Weight (MTOW) of 17,840 lb. Performance specifications included a maximum speed of 570 miles per hour, a range out to 960 miles, and a service ceiling up to 42,640 feet. Rate-of-climb reached 4,500 feet per minute.
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