Zobrazeno 1 - 10
of 26
pro vyhledávání: '"Jongwook Joo"'
Publikováno v:
Journal of Turbomachinery. 142
A combined experimental and analytical modeling effort has been carried out to measure the skin friction response of the boundary layer in high Reynolds number adverse pressure gradient flow. The experiment was conducted in the United Technologies Re
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::253acb64aca749fe0428ab0f8037bde0
https://doi.org/10.1115/1.4045166
https://doi.org/10.1115/1.4045166
Publikováno v:
Journal of Propulsion and Power. 33:522-530
A computational fluid dynamics-based analysis has been performed to assess propulsive efficiency benefits of a boundary layer ingesting propulsion system. This analysis is based on a full-scale con...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::35e0b33b36eb9f4fd6d91231aa24de35
https://doi.org/10.2514/1.b36069
https://doi.org/10.2514/1.b36069
Publikováno v:
Volume 2C: Turbomachinery.
In this paper, wall-resolved LES computations for a compressor cascade from Ecole Centrale de Lyon [1] are presented. A computational grid containing about 600 million computational cells was used in these simulations. This grid resolves the details
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::09b58fd1403767d6a4049d28644b4d2d
https://doi.org/10.1115/gt2018-77144
https://doi.org/10.1115/gt2018-77144
Publikováno v:
Journal of Fluids Engineering. 140
An efficient large-eddy simulation (LES) approach is investigated for laminar-to-turbulent transition in boundary layers. This approach incorporates the boundary-layer stability theory. Primary instability and subharmonic perturbations determined by
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8917e4ce5a56ee03631de8e9511a6631
https://doi.org/10.1115/1.4039865
https://doi.org/10.1115/1.4039865
Publikováno v:
2018 AIAA Aerospace Sciences Meeting.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::69ae68ada71645bae8389cdb352815fb
https://doi.org/10.2514/6.2018-1549
https://doi.org/10.2514/6.2018-1549
Publikováno v:
Volume 2B: Turbomachinery.
Large eddy simulations over a NACA65 compressor cascade with roughness were performed for multiple roughness heights. The experiments show flow separation as airfoil roughness is increased. In LES computations, surface roughness was represented by re
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::5ea3ad72c8b651e5c25e72e1011fe2cf
https://doi.org/10.1115/gt2017-64889
https://doi.org/10.1115/gt2017-64889
Publikováno v:
Volume 2C: Turbomachinery.
Surface roughness can make boundary-layers separate in diffusing flow. Most roughness Reynolds Averaged Navier Stokes (RANS) models which change the boundary conditions to model the roughness effects cannot predict this phenomenon. In this study, Lar
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0ddd77f713958c86c4284ae5022d93e0
https://doi.org/10.1115/gt2016-57912
https://doi.org/10.1115/gt2016-57912
Publikováno v:
Volume 2D: Turbomachinery.
It is important to be able to predict the state of the boundary layer on a high-pressure turbine vane with incoming turbulence. The laminar-to-turbulent transition significantly changes the heat transfer on the blade, which impacts the turbine perfor
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d49276427f2e95563c83f1b078d6d4da
https://doi.org/10.1115/gt2016-56980
https://doi.org/10.1115/gt2016-56980
Publikováno v:
Journal of Turbomachinery. 138
In the 1950s, NACA conducted a series of low-speed cascade experiments investigating the performance of NACA 65-series compressor cascades with tests covering multiple airfoils of varying camber and with variations in solidity and air inlet angle. Mo
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::4352481c1f6362d0e4f819ce3efc3925
https://doi.org/10.1115/1.4033514
https://doi.org/10.1115/1.4033514
Autor:
Paul A. Durbin, Jongwook Joo
Publikováno v:
Flow, Turbulence and Combustion. 88:407-430
Mode interaction is studied via direct numerical simulations of a Mach 4.5 boundary layer with discrete and continuous modes imposed at the inflow. An approximate decoupling procedure is developed to create separate vortical, acoustic and entropic co
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::92233e105ec022f8ed6d3c13e09b3953
https://doi.org/10.1007/s10494-011-9372-x
https://doi.org/10.1007/s10494-011-9372-x