I started to wonder NASA:s sldes about using LENR in JET and space engines. My concern is heat transfer from reactor to air.
Jet planes have pretty powerful engines, and they operate purely by heating incoming cold (+40...-50) air to hot air (800C?) which expands causing needed thrust.
-Kerosine 77000kg Airbus 300
-Flight time 14,5h
-Energy 42.8 MJ/kg (Kerosene)
=> Flight average power 63.13 MW! (In ideal engine like ramjet, but in real is somewhat less 50MW?)
If convection would be conservative 200W/m2/K and temp diff would be 500C (1300C-800C) that would require roughly 500m2 convection surface
(when assuming that high speed air would really be able to capture heat with that 200w/m2/K from reactor surface,
Taking heat directly from burning kerosine gets all energy to heating and that minus compressor etc. produces thrust power, but hard to believe that LENR engine efficiency would be equal nor better than Kerosene powered engine.
Anyone having better calculations?