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![Cover image for Validation of high aspect ratio cooling in a 89 kN (20,000 lb[sub f] thrust combustion chamber](/images/no-cover.png)
Validation of high aspect ratio cooling in a 89 kN (20,000 lb[sub f] thrust combustion chamber
| Location | Call # | Status |
|---|---|---|
| Joyner - Microforms B300 | NAS 1.15:107270 | ✔ Available |
Comparison of high aspect ratio cooling channel designs for a rocket combustion chamber with development of an optimized design
| Location | Call # | Status |
|---|---|---|
| Joyner - Microforms B300 | NAS 1.15:1998-206313 | ✔ Available |
Benefits of In Situ propellant utilization for a Mars sample return mission
| Location | Call # | Status |
|---|---|---|
| Joyner - Microforms B300 | NAS 1.15:106243 | ✔ Available |