Analysis of shock unsteadiness in a supersonic over-expanded planar nozzle
| العنوان: | Analysis of shock unsteadiness in a supersonic over-expanded planar nozzle |
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| المؤلفون: | Shashi B. Verma, Abdellah Hadjadj, Manisankar Chidambaranathan |
| المساهمون: | CSIR-National Aerospace Laboratories - NAL (INDIA), Complexe de recherche interprofessionnel en aérothermochimie (CORIA), Centre National de la Recherche Scientifique (CNRS)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU) |
| المصدر: | European Journal of Mechanics-B/Fluids European Journal of Mechanics-B/Fluids, Elsevier, 2018, 68, pp.55-65. ⟨10.1016/j.euromechflu.2017.11.005⟩ |
| بيانات النشر: | HAL CCSD, 2018. |
| سنة النشر: | 2018 |
| مصطلحات موضوعية: | 020301 aerospace & aeronautics, Materials science, Shock (fluid dynamics), Turbulence, Nozzle, General Physics and Astronomy, Resonance, Laminar flow, 02 engineering and technology, Mechanics, 01 natural sciences, 010305 fluids & plasmas, [SPI.MECA.MEFL]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Fluids mechanics [physics.class-ph], Physics::Fluid Dynamics, symbols.namesake, Boundary layer, 0203 mechanical engineering, Mach number, 0103 physical sciences, symbols, Supersonic speed, Mathematical Physics, ComputingMilieux_MISCELLANEOUS |
| الوصف: | An experimental investigation has been conducted to study the unsteady nature of the shock structure in an over-expanded planar nozzle. The main emphasis was to investigate (i) the effect of resonance associated with laminar shock-wave/boundary-layer interactions on the unsteady characteristics of the wall pressure signals in the region of the interaction and, (ii) the change in these characteristics as the state of boundary layer undergoes transition to turbulence and a resonance free interaction. The tests were conducted in a Mach 2 planar nozzle with wall-half angle of 5 . 7 ∘ . For almost all the NPR for which the nozzle is tested, the boundary layer state is seen to be in the laminar/transitional range and exhibits resonance for nozzle pressure ratios less than 2.3. The resonance tones associated with the laminar interactions result in a considerable increase in the length of the intermittent region. However, as the boundary layer state goes into the transitional regime and the resonance tones disappear, the length of intermittent region is seen to decrease significantly. A decrease in this length also causes the peak standard deviation values to decrease. Further a free interaction region is observed for separated nozzle flows irrespective of the NPR of operation for resonance free interactions. |
| اللغة: | English |
| تدمد: | 0997-7546 1873-7390 |
| DOI: | 10.1016/j.euromechflu.2017.11.005⟩ |
| URL الوصول: | https://explore.openaire.eu/search/publication?articleId=doi_dedup___::80f3894bf13466622e2895b99dc02529 https://hal.archives-ouvertes.fr/hal-02088403 |
| Rights: | CLOSED |
| رقم الانضمام: | edsair.doi.dedup.....80f3894bf13466622e2895b99dc02529 |
| قاعدة البيانات: | OpenAIRE |
| تدمد: | 09977546 18737390 |
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| DOI: | 10.1016/j.euromechflu.2017.11.005⟩ |