| タイトル | HUD - PREDICTION OF BOUNDARY-LAYER DEVELOPMENT ON TWO-DIMENSIONAL OR AXISYMETRIC BODIES |
| 著者（英） | Pinckney, S. Z. |
| 発行日 | 1994-01-01 |
| 言語 | eng |
| 内容記述 | HUD is an integral code based on the Spaulding-Chi method for predicting boundary-layer development in laminar, transitional, and turbulent flow regions on two-dimensional or axisymetric bodies. This program was developed using integral-momentum, moment-of-momentum, and energy equations and has the capability of approximating non-equilibrium velocity profiles as well as the local surface friction in the presence of a pressure gradient. An approach was also developed for predicting heat transfer in a turbulent boundary layer in the presence of a high axial pressure gradient. Provisions are included for pressure gradients normal and lateral to the surface. The program is designed with particular emphasis on its applicability to supersonic combustion, thus, real gas flow effects were included. The resulting method permits estimation of cooling requirements for scramjet engines. Because of this capability, the HUD program has been incorporated into several scramjet cycle performance analysis codes including SCRAM (ARC-12338) and SRGULL (LEW-15093). HUD is written in machine independent FORTRAN 77 and should be portable to any computer with a valid FORTRAN compiler. On an IBM PC compatible under MS-DOS, HUD requires 145K RAM. The program is available on a 5.25 inch 360K MS-DOS diskette. HUD was developed in 1970 and last updated in 1991. IBM PC is a registered trademark of International Business Machines Corporation. MS-DOS is a registered trademark of Microsoft Corporation. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 94M10484
LEW-15163 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/312587 |
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