Development and testing of ablative rocket engine with selected 7.62 cm /3.0 in./ diameter throat inserts, and testing of zirconia reinforced with tungsten-rhenium wire for throat insert material
Development and testing of ablative rocket engine with selected 7.62-centimeter /3.0 in/ diameter throat inserts
1971-07-01
Report
No indication
English
Improved Throat Inserts for Ablative Thrust Chambers
NTIS | 1967
|Improved throat inserts for ablative thrust chambers
NTRS | 1967
|