J85 General Electric Turbojet Engine

The design team wrapped a small highly aerodynamic fighter around two compact and high thrust general electric j85 engines focusing on performance and a low cost of maintenance.

J85 general electric turbojet engine.

On november 28 1954 general electric was awarded a usaf development. Afterburning variants can reach up to 5 000 lb f 22 kn. The gen eral elec tric j85 is a small sin gle shaft tur bo jet en gine. The en gine de pend ing upon ad di tional equip ment and spe cific model weighs from 300 to 500 pounds 140 to 230 kg.

The general electric cj610 is a non afterburning turbojet engine derived from the military j85 and is used on a number of civilian business jets. Military versions produce up to 2 950 lbf 13 1 kn of thrust dry. The engine depending upon additional equipment and specific model weighs from 300 to 500 pounds 140 to 230 kg. The prototype j85 engine ran in january 1956 the first flight was in august 1958 as the power plant of the mcdonnell gam 72 missile and in september 1958 the prototype north american t 39 sabreliner flew for the first time powered by the first man rated j85 engines.

Mil i tary ver sions pro duce up to 2 950 lb f 13 1 kn of thrust dry af ter burn ing vari ants can reach up to 5 000 lb f 22 kn. Afterburning variants can reach up to 5 000 lbf 22 kn. The general electric j85is a small single shaft turbojet engine. The j85 is a single shaft turbojet engine built by.

Military versions produce up to 2 950 lb f 13 1 kn of thrust dry. The general electric j85 is a small single shaft turbojet engine. The engine depending upon additional equipment and specific model weighs from 300 to 500 pounds 140 to 230 kg. Military versions produce up to 2 950 lbf13 kn of thrust dry afterburning variants can reach up to 5 000 lbf 22 kn.

The general electric j85 is a small single shaft turbojet engine. In late 1953 general electric began a design study of a high thrust to weight ratio turbojet engine.