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Extension of boundary-layer heat-transfer theory to cooled turbine blades
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1950 |
| Description | An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades. |
| File Size | 2910173 |
| Page Count | 53 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930086192 |
| Archival Resource Key | ark:/13960/t4xh3xx8q |
| Language | English |
| Publisher Date | 1950-08-11 |
| Access Restriction | Open |
| Subject Keyword | Heat Transfer, Aerodynamic Flow, Viscous 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 |
