Determination of the critical reynolds number for flow over symmetric NACA airfoils

Name: Determination of the critical reynolds number for flow over symmetric NACA airfoils
Author: Yousefi, K., Razeghi, Alireza

İsim	Determination of the critical reynolds number for flow over symmetric NACA airfoils
Yazar	Yousefi, K., Razeghi, Alireza
Basım Tarihi:	2018
Basım Yeri	- American Institute of Aeronautics and Astronautics Inc, AIAA
Tür	Belge
Dil	İngilizce
Dijital	Evet
Yazma	Hayır
Kütüphane:	Özyeğin Üniversitesi
Demirbaş Numarası	978-162410524-1
Kayıt Numarası	52fd8b62-dd30-498c-bdd6-a2b7203f0753
Tarih	2018
Örnek Metin	The determination of the critical Reynolds number is of practical importance in many engineering applications, particularly in determining the aerodynamic characteristics of air vehicles. In this study, we numerically investigated the laminar-turbulent transition location over NACA 0012, 0015, and 0018 airfoil profiles in order to determine their lower critical Reynolds number. To this end, a CFD FORTRAN code was developed based on the hybrid viscous-inviscid interaction method with an incorporated eN transition method to model the boundary layer flow around airfoil profiles. The results, in general, indicated that the laminar-turbulent transition location over an airfoil is strongly dependent on the Reynolds number and moves toward the downstream as the Reynolds number decreases. The lower critical Reynolds number was then defined as the velocity at which the flow becomes laminar over the airfoil, which corresponds to the conditions that the transition point located at the trailing edge of the airfoil. The lower critical Reynolds number for flow over NACA 0012, 0015, and 0018 airfoils were, therefore, determined to be 1 × 105, 5 × 104, and 3.5 × 104, respectively. Moreover, the variations of the transition location with the angle of the attack showed that the transition point moves toward the leading edge of the airfoil as the angle of attack increases.
DOI	10.2514/6.2018-0818

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Determination of the critical reynolds number for flow over symmetric NACA airfoils

Yazar Yousefi, K., Razeghi, Alireza

Basım Tarihi 2018

Basım Yeri - American Institute of Aeronautics and Astronautics Inc, AIAA

Tür Belge

Dil İngilizce

Dijital Evet

Yazma Hayır

Kütüphane Özyeğin Üniversitesi

Demirbaş Numarası 978-162410524-1

Kayıt Numarası 52fd8b62-dd30-498c-bdd6-a2b7203f0753

Tarih 2018

Örnek Metin The determination of the critical Reynolds number is of practical importance in many engineering applications, particularly in determining the aerodynamic characteristics of air vehicles. In this study, we numerically investigated the laminar-turbulent transition location over NACA 0012, 0015, and 0018 airfoil profiles in order to determine their lower critical Reynolds number. To this end, a CFD FORTRAN code was developed based on the hybrid viscous-inviscid interaction method with an incorporated eN transition method to model the boundary layer flow around airfoil profiles. The results, in general, indicated that the laminar-turbulent transition location over an airfoil is strongly dependent on the Reynolds number and moves toward the downstream as the Reynolds number decreases. The lower critical Reynolds number was then defined as the velocity at which the flow becomes laminar over the airfoil, which corresponds to the conditions that the transition point located at the trailing edge of the airfoil. The lower critical Reynolds number for flow over NACA 0012, 0015, and 0018 airfoils were, therefore, determined to be 1 × 105, 5 × 104, and 3.5 × 104, respectively. Moreover, the variations of the transition location with the angle of the attack showed that the transition point moves toward the leading edge of the airfoil as the angle of attack increases.

DOI 10.2514/6.2018-0818