I realize this may sound a little ambitious , but since I’m not going into space I thought I would at least do an initial feasibility study on the following project that a small dedicated group would like to embark on : A compact geared high bypass Turbofan engine with a Static thrust @ Sea Level of about 150Kg (1500N or 330Lbs) The engine core (@ 100000rpm) is driving a two stage LP spool with a potential output of 60-80 SHP (34-60 KW) which should drive a geared 40cm (16in) diameter Fan stage (8-9cm Hub) @15000rpm (to keep blade tip speeds at or below Mach 1). The fan stage would be very similar to what can be seen in the PW610F powering the Eclipse: http://m1.ikiwq.com/img/xl/wK6FwxQhflSqML9VywJ6Xc.jpg [Broken] Since regular prop configurations were getting about 4 - 4.5 Lbs of thrust per SHP, I hoped that this would do the trick. Somebody was kind enough to send me a generic spreadsheet that calculates thrust , and it seems that I can only achieve roughly 175Lbs of static thrust in this configuration :( However in this spreadsheet, wide cord blades, or varying the Fan RPM didn’t seem to change anything (which seems odd ?). So I am hoping if someone could just confirm roughly if this may still be possible in this configuration in any way, or if I am forced to go the Turbo-Prop route ?