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A feasibility study of heat-pipe-cooled leading edges for hypersonic cruise aircraft
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Silverstein, C. C. |
| Copyright Year | 1971 |
| Description | A theoretical study of the use of heat pipe structures for cooling the leading edges of hypersonic cruise aircraft was carried out over a Mach number range of 6 to 12. Preliminary design studies showed that a heat pipe cooling structure with a 33-in. chordwise length could maintain the maximum temperature of a 65 deg sweepback wing with a 0.5-in. leading edge radius below 1600 F during cruise at Mach 8. A few relatively minor changes in the steady-state design of the structure were found necessary to insure satisfactory cooling during the climb to cruise speed and altitude. It was concluded that heat pipe cooling is an attractive, feasible technique for limiting leading edge temperatures of hypersonic cruise aircraft. |
| File Size | 6004359 |
| Page Count | 151 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720005300 |
| Archival Resource Key | ark:/13960/t8md3ph6r |
| Language | English |
| Publisher Date | 1971-11-01 |
| Access Restriction | Open |
| Subject Keyword | Thermodynamics And Combustion Cooling Systems Thermal Protection Hypersonic Aircraft Leading Edges Heat Pipes Aerodynamic Heating 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 |
