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Thermal analysis and design of a cooling system for a mach 14 nozzle
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Mullisen, Ronald Kaste, Keith |
| Copyright Year | 1987 |
| Description | The analysis and design of a Mach 14 converging diverging nozzle wall liner is provided. The analysis indicates that: no fin on the coolant side of the nozzle wall is optimum, the thermal stresses are dominant, and the critical area is very near the throat. The molybdenum alloy TZM, with a wall thickness of 2.0 mm in the throat area, appears to be the only material capable of meeting design requirements. Additionally, cooling water at 2000 psia with a flow velocity of 25 m/s in the coolant passages is required. |
| File Size | 2637698 |
| Page Count | 99 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870005838 |
| Archival Resource Key | ark:/13960/t76t5jt80 |
| Language | English |
| Publisher Date | 1987-01-30 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Throats Nozzle Walls Nozzle Inserts Convergent-divergent Nozzles Cooling Systems Wind Tunnel Nozzles Hypersonic Nozzles Thermal Analysis Design Analysis Molybdenum Alloys Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
