Loading...
Please wait, while we are loading the content...
Similar Documents
Evaluation of active cooling systems for a mach 6 hypersonic transport airframe, part 2
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Anthony, F. M. McConarty, W. A. Helenbrook, R. G. |
| Copyright Year | 1971 |
| Description | Transpiration and convective cooling concepts are examined for the fuselage and tail surface of a Mach 6 hypersonic transport aircraft. Hydrogen, helium, and water are considered as coolants. Heat shields and radiation barriers are examined to reduce heat flow to the cooled structures. The weight and insulation requirements for the cryogenic fuel tanks are examined so that realistic totals can be estimated for the complete fuselage and tail. Structural temperatures are varied to allow comparison of aluminum alloy, titanium alloy, and superalloy contruction materials. The results of the study are combined with results obtained on the wing structure, obtained in a previous study, to estimate weights for the complete airframe. The concepts are compared among themselves, and with the uncooled concept on the basis of structural weight, cooling system weight, and coolant weight. |
| File Size | 7962932 |
| Page Count | 196 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720014374 |
| Archival Resource Key | ark:/13960/t3sv2bm9p |
| Language | English |
| Publisher Date | 1971-12-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Equipment Specifications Transport Aircraft Systems Engineering Heat Shielding Cooling Systems Temperature Control Thermodynamic Properties Hypersonic Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
