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Calculation of transonic flow in a linear cascade
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Donovan, L. F. |
| Copyright Year | 1984 |
| Description | Turbomachinery blade designs are becoming more aggressive in order to achieve higher loading and greater range. New analysis tools are required to cope with these heavily loaded blades that may operate with a thin separated region near the trailing edge on the suction surface. An existing, viscous airfoil code was adapted to cascade conditions in an attempt to provide this capability. Comparisons with recently obtained data show that calculated and experimental surface Mach numbers were in good agreement but loss coefficients and outlet air angles were not. |
| File Size | 442437 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840016471 |
| Archival Resource Key | ark:/13960/t4km44h3q |
| Language | English |
| Publisher Date | 1984-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Navier-stokes Equation Turbomachine Blades Cascade Flow Transonic Flow Algorithms Finite Difference Theory Flow Distribution Trailing Edges Turbomachinery Airfoils Computer Programs Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
