I know it was a low-bypass continuously-afterburning turbofan, designed primarily for the L-2000-7A SST.
I'm just wondering if there is any more information available on this engine?
|Quoting B2707SST (Reply 3):|
The JTF17A-21L proposed for the Lockheed L-2000 was a low-bypass turbofan with afterburning capability in the bypass duct only (a "duct-burning turbofan"). It was to generate 60,760 lbs. of augmented or 38,130 lbs. of non-augmented thrust at takeoff. Bypass ratio was 1.3:1.