Three propulsion systems for a Mach 2 STOVL fighter were compared. The three propulsion systems are: (1) turbine bypass engine with a turbocompressor used for STOVL only; (2) turbine bypass engine with a turbocompressor for both STOVL and thrust during forward flight; and (3) mixed flow afterburning turbofan with a remote burner lift system. In the first system, the main engines have afterburners and the turbocompressors use afterburning during STOVL. In the second system, the turbine bypass engines are dry and the turbocompressors have afterburners. The mission used in the study is a deck launched intercept mission. It is indicated that large improvements in combat time are possible when the turbocompressors are used for both left and thrust for forward flight. Previously announced in STAR as N84-24582
Supersonic STOVL aircraft with turbine bypass/turbo-compressor engines
01.06.1984
Aufsatz (Konferenz)
Keine Angabe
Englisch
Supersonic STOVL research aircraft
NTRS | 1982
|Supersonic STOVL Research Aircraft
SAE Technical Papers | 1982
|