| タイトル | An Investigation of Transonic Resonance in a Mach 2.2 Round Convergent-Divergent Nozzle |
| 本文（外部サイト） | http://hdl.handle.net/2060/20150002103 |
| 著者（英） | Dippold, Vance F., III; Zaman, Khairul B. M. Q. |
| 著者所属（英） | NASA Glenn Research Center |
| 発行日 | 2015-01-05 |
| 言語 | eng |
| 内容記述 | Hot-wire and acoustic measurements were taken for a round convergent nozzle and a round convergent-divergent (C-D) nozzle at a jet Mach number of 0.61. The C-D nozzle had a design Mach number of 2.2. Compared to the convergent nozzle jet flow, the Mach 2.2 nozzle jet flow produced excess broadband noise (EBBN). It also produced a transonic resonance tone at 1200 Herz. Computational simulations were performed for both nozzle flows. A steady Reynolds-Averaged Navier-Stokes simulation was performed for the convergent nozzle jet flow. For the Mach 2.2 nozzle flow, a steady RANS simulation, an unsteady RANS (URANS) simulation, and an unsteady Detached Eddy Simulation (DES) were performed. The RANS simulation of the convergent nozzle showed good agreement with the hot-wire velocity and turbulence measurements, though the decay of the potential core was over-predicted. The RANS simulation of the Mach 2.2 nozzle showed poor agreement with the experimental data, and more closely resembled an ideally-expanded jet. The URANS simulation also showed qualitative agreement with the hot-wire data, but predicted a transonic resonance at 1145 Herz. The DES showed good agreement with the hot-wire velocity and turbulence data. The DES also produced a transonic tone at 1135 Herz. The DES solution showed that the destabilization of the shock-induced separation region inside the nozzle produced increased levels of turbulence intensity. This is likely the source of the EBBN. |
| NASA分類 | Aerodynamics; Aircraft Propulsion and Power; Fluid Mechanics and Thermodynamics |
| レポートNO | GRC-E-DAA-TN19364 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/60652 |
