Abo Bibliothek: Guest
International Journal of Fluid Mechanics Research

Erscheint 6 Ausgaben pro Jahr

ISSN Druckformat: 2152-5102

ISSN Online: 2152-5110

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 1.1 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 1.3 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.0002 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.33 SJR: 0.256 SNIP: 0.49 CiteScore™:: 2.4 H-Index: 23

Indexed in

A Numerical Study on the Control of Self-Excited Shock Induced Oscillation in Transonic Flow around a Supercritical Airfoil

Volumen 41, Ausgabe 5, 2014, pp. 440-459
DOI: 10.1615/InterJFluidMechRes.v41.i5.50
Get accessGet access

ABSTRAKT

Self-excited shock induced oscillation (SIO) around an airfoil is observed in transonic flows at certain conditions of free stream Mach number and angle of attack. At these conditions, the interaction of unsteady shock wave with airfoil boundary layer becomes complex and causes several detrimental effects such as the fluctuating lift and drag coefficients, aeroacoustic noise and vibration, high cycle fatigue failure (HCF), buffeting and so on. In the present study, Reynolds Averaged Navier-Stokes equations have been used to predict the aerodynamics behaviour over a NASA SC(2) 0714 supercritical airfoil in transonic flow conditions. To suppress the unsteady aerodynamic behaviour, a shock control bump is introduced at the mean shock position. Computations have been performed at free stream Mach number of 0.77 while the angle of attack was varied from 2° to 7°. The results obtained from the numerical computation have been validated with the experimental results. Mach contour, lift and drag coefficient, and pressure history over the airfoil surface have been analyzed for the cases of baseline airfoil and airfoil with bump. It is found that, the bump can control the unsteady SIO in the flow field.

REFERENZIERT VON
  1. Rahman Muhammad Rizwanur, Labib Mohammad Itmam, Hasan Abul Bashar Mohammad Toufique, Joy Mohammad Saddam Hossain, Setoguchi Toshiaki, Kim Heuy Dong, Control of Transonic Shock Wave Oscillation over a Supercritical Airfoil, Open Journal of Fluid Dynamics, 05, 04, 2015. Crossref

  2. Rahman M. Rizwanur, Labib Md. Itmam, Hasan A. B. M. Toufique, Ali M., Mitsutake Y., Setoguchi T., Effect of cavity on shock oscillation in transonic flow over RAE2822 supercritical airfoil, 1754, 2016. Crossref

1162 Artikelansichten 48 Artikel-Downloads Metriken
1162 ANSICHTEN 48 HERUNTERLADEN 2 Crossref ZITATE Google
Scholar
ZITATE

Artikel mit ähnlichem Inhalt:

NUMERICAL INVESTIGATION FOR SELECTION OF AIRFOIL WITH REGARD TO FLYING WING APPLICATIONS International Journal of Fluid Mechanics Research, Vol.49, 2022, issue 5
Sandhya S. Rani, G. R. Rakshith, V. Somashekar, Chaitra Shashikant Paragi, Sachin R. Raj
EXPERIMENTAL INVESTIGATIONS OF WING LIFT CONTROL BY ACTUATORS DISTRIBUTED ON THE WING SURFACE TsAGI Science Journal, Vol.48, 2017, issue 1
Andrey Yuryevich Urusov, Maxim Vladimirovich Ustinov, Jacob Shmerkovich Flaxman, Aleksandr Gennadievich Nalivaiko, Aleksandr Aleksandrovich Uspenskii
THE HIGH-SPEED FLOW STABILITY (HSFS) SOFTWARE PACKAGE FOR STABILITY ANALYSIS OF COMPRESSIBLE BOUNDARY LAYERS TsAGI Science Journal, Vol.48, 2017, issue 3
A. V. Fedorov, Anton Olegovich Obraz
Numerical analyses of re-entry module - Apex cover separation aerodynamics at subsonic Mach number Proceedings of the 26thNational and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference December 17-20, 2021, IIT Madras, Chennai-600036, Tamil Nadu, India, Vol.0, 2021, issue
Amit Kumar Singh, M.M. Patil, V. Ashok, B.Venkat Shivaram Jadav, G Vidya
Comparison of wake characteristics behind a custom designed airfoil performing different types of flapping oscillations Proceedings of the 26thNational and 4th International ISHMT-ASTFE Heat and Mass Transfer Conference December 17-20, 2021, IIT Madras, Chennai-600036, Tamil Nadu, India, Vol.0, 2021, issue
Devendra Kumar Patel, V K Vineeth
Digitales Portal Digitale Bibliothek eBooks Zeitschriften Referenzen und Berichte Forschungssammlungen Preise und Aborichtlinien Begell House Kontakt Language English 中文 Русский Português German French Spain