| contributor author | T. H. Okiishi | |
| contributor author | G. J. Walker | |
| contributor author | H. P. Hodson | |
| contributor author | H.-W. Shin | |
| contributor author | D. E. Halstead | |
| contributor author | D. C. Wisler | |
| date accessioned | 2017-05-08T23:55:14Z | |
| date available | 2017-05-08T23:55:14Z | |
| date copyright | January, 1997 | |
| date issued | 1997 | |
| identifier issn | 0889-504X | |
| identifier other | JOTUEI-28657#128_1.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/119666 | |
| description abstract | This is Part Four of a four-part paper. It begins with Section 16.0 and concludes the description of the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer development on airfoil surfaces in multistage turbomachinery. In this part, the computational predictions made using several modern boundary layer codes are presented. Both steady codes and an unsteady code were evaluated. The results are compared with time-averaged and unsteady integral parameters measured for the boundary layers. Assessments are made to provide guidance in using the predictive codes to locate transition and predict loss. Conclusions from the computational analyses are then presented. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Boundary Layer Development in Axial Compressors and Turbines: Part 4 of 4—Computations and Analyses | |
| type | Journal Paper | |
| journal volume | 119 | |
| journal issue | 1 | |
| journal title | Journal of Turbomachinery | |
| identifier doi | 10.1115/1.2841001 | |
| journal fristpage | 128 | |
| journal lastpage | 139 | |
| identifier eissn | 1528-8900 | |
| keywords | Compressors | |
| keywords | Boundary layers | |
| keywords | Turbines | |
| keywords | Computation | |
| keywords | Turbomachinery AND Airfoils | |
| tree | Journal of Turbomachinery:;1997:;volume( 119 ):;issue: 001 | |
| contenttype | Fulltext | |