TY  - JOUR
AU  - Abobaker, Mostafa
AU  - Petrović, Zlatko
AU  - Fotev, Vasko
AU  - Toumi, Noureddine
AU  - Ivanović, Ivana
PY  - 2017
UR  - https://machinery.mas.bg.ac.rs/handle/123456789/2516
AB  - Assessment of airfoil aerodynamic characteristics is essential part of any optimal airfoil design procedure. This paper illustrates rapid and efficient method for determination of aerodynamic characteristics of an airfoil, which is based on viscous-inviscid interaction. Inviscid flow is solved by conformal mapping, while viscous effects are determined by solving integral boundary layer equations. Displacement thickness is iteratively added to the airfoil contour by alternating inviscid and viscous solutions. With this approach efficient method is developed for airfoil design by shape perturbations. The procedure is implemented in computer code, and calculation results are compared with results of XFOIL calculations and with experiment. Eppler E387 low Reynolds number airfoil and soft stall S8036 airfoil are used for verification of developed procedure for Reynolds numbers 200000, 350000, and 500000. Calculated drag polars are presented in this paper and good agreement with experiment is achieved as long as small separation is maintained. Calculated positions of laminar separation, reattachment, and turbulent separation closely follow experimental measurement. The calculations are performed in relatively short time, which makes this approach suitable for low Reynolds number airfoil design.
PB  - Univ Osijek, Tech Fac, Slavonski Brod
T2  - Tehnički vjesnik
T1  - Aerodynamic characteristics of low reynolds number airfoils
EP  - 118
IS  - 1
SP  - 111
VL  - 24
DO  - 10.17559/TV-20160225100019
ER  - 

@article{
author = "Abobaker, Mostafa and Petrović, Zlatko and Fotev, Vasko and Toumi, Noureddine and Ivanović, Ivana",
year = "2017",
abstract = "Assessment of airfoil aerodynamic characteristics is essential part of any optimal airfoil design procedure. This paper illustrates rapid and efficient method for determination of aerodynamic characteristics of an airfoil, which is based on viscous-inviscid interaction. Inviscid flow is solved by conformal mapping, while viscous effects are determined by solving integral boundary layer equations. Displacement thickness is iteratively added to the airfoil contour by alternating inviscid and viscous solutions. With this approach efficient method is developed for airfoil design by shape perturbations. The procedure is implemented in computer code, and calculation results are compared with results of XFOIL calculations and with experiment. Eppler E387 low Reynolds number airfoil and soft stall S8036 airfoil are used for verification of developed procedure for Reynolds numbers 200000, 350000, and 500000. Calculated drag polars are presented in this paper and good agreement with experiment is achieved as long as small separation is maintained. Calculated positions of laminar separation, reattachment, and turbulent separation closely follow experimental measurement. The calculations are performed in relatively short time, which makes this approach suitable for low Reynolds number airfoil design.",
publisher = "Univ Osijek, Tech Fac, Slavonski Brod",
journal = "Tehnički vjesnik",
title = "Aerodynamic characteristics of low reynolds number airfoils",
pages = "118-111",
number = "1",
volume = "24",
doi = "10.17559/TV-20160225100019"
}

Abobaker, M., Petrović, Z., Fotev, V., Toumi, N.,& Ivanović, I.. (2017). Aerodynamic characteristics of low reynolds number airfoils. in Tehnički vjesnik
Univ Osijek, Tech Fac, Slavonski Brod., 24(1), 111-118.
https://doi.org/10.17559/TV-20160225100019

Abobaker M, Petrović Z, Fotev V, Toumi N, Ivanović I. Aerodynamic characteristics of low reynolds number airfoils. in Tehnički vjesnik. 2017;24(1):111-118.
doi:10.17559/TV-20160225100019 .

Abobaker, Mostafa, Petrović, Zlatko, Fotev, Vasko, Toumi, Noureddine, Ivanović, Ivana, "Aerodynamic characteristics of low reynolds number airfoils" in Tehnički vjesnik, 24, no. 1 (2017):111-118,
https://doi.org/10.17559/TV-20160225100019 . .