| タイトル | Boundary-Layer Code For Supersonic Combustion |
| 著者（英） | Pinckney, S. Z.; Walton, J. T. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1994-05-01 |
| 言語 | eng |
| 内容記述 | HUD is integral computer code based on Spaulding-Chi method for predicting development of boundary layers in laminar, transitional, and turbulent regions of flows on two-dimensional or axisymmetric bodies. Approximates nonequilibrium velocity profiles as well as local surface friction in presence of pressure gradient. Predicts transfer of heat in turbulent boundary layer in presence of high axial presure gradient. Provides for pressure gradients both normal and lateral to surfaces. Also used to estimate requirements for cooling scramjet engines. Because of this capability, HUD program incorporated into several scramjet-cycle-performance-analysis codes, including SCRAM (ARC-12338) and SRGULL (LEW-15093). Written in FORTRAN 77. |
| NASA分類 | MECHANICS |
| レポートNO | 94B10264
LEW-15163 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/313336 |
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