| タイトル | Effects of turbulence compressibility and unsteadiness in compression corner flow |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950014635 |
| 著者（英） | Brankovic, A.; Zeman, O. |
| 著者所属（英） | Pratt and Whitney Aircraft |
| 発行日 | 1994-12-01 |
| 言語 | eng |
| 内容記述 | The structure of the separated flow region over a 20 degree compression corner at a free-stream Mach number of 2.84 is investigated computationally using a Reynolds averaged Navier Stokes (R.A.N.S.) solver and kappa-epsilon model. At this Mach number and ramp angle, a steady-state recirculation region of order delta(sub o) is observed, with onset of a 'plateau' in the wall pressure distribution near the corner. At lower ramp angles, separation is negligible, while at an angle of 24 degrees, separation regions of length 2 delta(sub o) are expected. Of interest here is the response of the mathematical model to inclusion of the pressure dilatation term for turbulent kinetic energy. Compared with the experimental data of Smits and Muck (1987), steady-state computations show improvement when the pressure dilatation term is included. Unsteady computations, using both unforced and then forced inlet conditions, did not predict the oscillatory motion of the separation bubble as observed in laboratory experiments. An analysis of the separation bubble oscillation and the turbulent boundary layer (T.B.L.) frequencies for this flow suggests that the bubble oscillations are of nearly the same order as the turbulent frequencies, and therefore difficult for the model to separate and resolve. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 95N21052 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/108539 |
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