Design of injectors and ablative thrust chambers for FLOX propane rocket engine with 1.2 inch throat diameter
Design of injectors and ablative thrust chambers for a flox-propane rocket engine with a 1.2-inch throat diameter
1969-07-01
Miscellaneous
No indication
English
Improved Throat Inserts for Ablative Thrust Chambers
NTIS | 1967
|Improved throat inserts for ablative thrust chambers
NTRS | 1967
|