Experimental research on blunt trailing-edge airfoil sections at low Reynolds numbers

AIAA Journal ◽  
1995 ◽  
Vol 33 (11) ◽  
pp. 2001-2005 ◽  
Author(s):  
Junzo Sato ◽  
Yasuto Sunada
Keyword(s):  
Experimental Research ◽  
Reynolds Numbers ◽  
Trailing Edge ◽  
Low Reynolds Numbers ◽  
Blunt Trailing Edge ◽  
Low Reynolds

scholarly journals Flow visualization over a thick blunt trailing-edge airfoil with base cavity at low Reynolds numbers using PIV technique

2016 ◽  
Vol 20 (4) ◽  
pp. 695-710 ◽  
Author(s):  
Gholamhossein Taherian ◽  
Mahdi Nili-Ahmadabadi ◽  
Mohammad Hassan Karimi ◽  
Mohammad Reza Tavakoli
Keyword(s):  
Flow Visualization ◽  
Reynolds Numbers ◽  
Trailing Edge ◽  
Low Reynolds Numbers ◽  
Blunt Trailing Edge ◽  
Piv Technique ◽  
Base Cavity ◽  
Low Reynolds

Aerodynamic Effects of Trailing Edge Serrations at Low Reynolds Numbers

2022 ◽  
Author(s):  
Israel Bron Simplicio ◽  
Giovanni F. Nino ◽  
Robert Breidenthal
Keyword(s):  
Reynolds Numbers ◽  
Trailing Edge ◽  
Low Reynolds Numbers ◽  
Low Reynolds ◽  
Trailing Edge Serrations

Investigation on the effect of leading edge tubercles of sweptback wing at low reynolds number

2020 ◽  
Vol 21 (6) ◽  
pp. 621
Author(s):  
Veerapathiran Thangaraj Gopinathan ◽  
John Bruce Ralphin Rose ◽  
Mohanram Surya
Keyword(s):  
Leading Edge ◽  
Reynolds Numbers ◽  
Sweep Angle ◽  
Laminar Separation ◽  
Low Reynolds Numbers ◽  
Flow Energy ◽  
Airplane Wing ◽  
Low Reynolds ◽  
Naca 0015 ◽  
Wing Performance

Aerodynamic efficiency of an airplane wing can be improved either by increasing its lift generation tendency or by reducing the drag. Recently, Bio-inspired designs have been received greater attention for the geometric modifications of airplane wings. One of the bio-inspired designs contains sinusoidal Humpback Whale (HW) tubercles, i.e., protuberances exist at the wing leading edge (LE). The tubercles have excellent flow control characteristics at low Reynolds numbers. The present work describes about the effect of tubercles on swept back wing performance at various Angle of Attack (AoA). NACA 0015 and NACA 4415 airfoils are used for swept back wing design with sweep angle about 30°. The modified wings (HUMP 0015 A, HUMP 0015 B, HUMP 4415 A, HUMP 4415 B) are designed with two amplitude to wavelength ratios (η) of 0.1 & 0.24 for the performance analysis. It is a novel effort to analyze the tubercle vortices along the span that induce additional flow energy especially, behind the tubercles peak and trough region. Subsequently, Co-efficient of Lift (CL), Co-efficient of Drag (CD) and boundary layer pressure gradients also predicted for modified and baseline (smooth LE) models in the pre & post-stall regimes. It was observed that the tubercles increase the performance of swept back wings by the enhanced CL/CD ratio in the pre-stall AoA region. Interestingly, the flow separation region behind the centerline of tubercles and formation of Laminar Separation Bubbles (LSB) were asymmetric because of the sweep.

Low Reynolds number flow around and heat transfer from a heated circular cylinder

2010 ◽  
Vol 1 (1-2) ◽  
pp. 15-20 ◽  
Author(s):  
B. Bolló
Keyword(s):  
Reynolds Number ◽  
Circular Cylinder ◽  
Lift Coefficient ◽  
Reynolds Numbers ◽  
Low Reynolds Numbers ◽  
Reynolds Number Flow ◽  
Two Dimensional Flow ◽  
Number Flow ◽  
Low Reynolds ◽  
Increasing Temperature

Abstract The two-dimensional flow around a stationary heated circular cylinder at low Reynolds numbers of 50 < Re < 210 is investigated numerically using the FLUENT commercial software package. The dimensionless vortex shedding frequency (St) reduces with increasing temperature at a given Reynolds number. The effective temperature concept was used and St-Re data were successfully transformed to the St-Reeff curve. Comparisons include root-mean-square values of the lift coefficient and Nusselt number. The results agree well with available data in the literature.

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