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Prediction method for two-dimensional aerodynamic losses of cooled vanes using integral boundary-layer parameters
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Augler, R. E. Goldman, L. J. |
| Copyright Year | 1980 |
| Description | A generalized analysis to predict the two-dimensional aerodynamic losses of film-cooled vanes by using integral boundary-layer parameters is presented. Heat-transfer and trailing-edge injection effects are included in the method. An approximate solution of the generalized equations is also included to show more clearly the effect of the different boundary-layer and cooling parameters on the losses. The analytical predictions agree well with the experimental results, indicating that available boundary-layer calculations for cooled vanes are of sufficient accuracy to use in the prediction method. |
| File Size | 1676173 |
| Page Count | 44 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800008770 |
| Archival Resource Key | ark:/13960/t3518t56m |
| Language | English |
| Publisher Date | 1980-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Losses Turbine Blades Trailing Edges Film Cooling Two Dimensional Flow Kinetic Energy Aerodynamic Characteristics Prediction Analysis Techniques Heat Transfer Boundary Layers Displacement Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
