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Design of injectors and ablative thrust chambers for a flox-propane rocket engine with a 1.2-inch throat diameter
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1969 |
| Description | Design of injectors and ablative thrust chambers for FLOX propane rocket engine with 1.2 inch throat diameter |
| File Size | 5450941 |
| Page Count | 39 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19690021182 |
| Archival Resource Key | ark:/13960/t2n63910m |
| Language | English |
| Publisher Date | 1969-07-01 |
| Access Restriction | Open |
| Subject Keyword | Propulsion Systems Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |