Hydrogen bubble flow visualization at low Reynolds numbers.

AIAA Journal ◽  
1969 ◽  
Vol 7 (8) ◽  
pp. 1635-1637 ◽  
Author(s):  
FREDERICK W. ROOS ◽  
WILLIAM W. WILLMARTH
Keyword(s):  
Flow Visualization ◽  
Reynolds Numbers ◽  
Bubble Flow ◽  
Hydrogen Bubble ◽  
Low Reynolds Numbers ◽  
Low Reynolds

S0504-1-5 Flow visualization and velocity measurement of a two-dimensional jet at low Reynolds numbers

2009 ◽  
Vol 2009.2 (0) ◽  
pp. 173-174
Author(s):  
Shohei NAMAITA ◽  
Jyunya KOIWAI ◽  
Yuki MUTOU ◽  
Akinori MURAMATSU ◽  
Tomohisa OHTAKE ◽  
...  
Keyword(s):  
Flow Visualization ◽  
Velocity Measurement ◽  
Reynolds Numbers ◽  
Two Dimensional ◽  
Low Reynolds Numbers ◽  
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

Flow Separation in an Aerofoil Cascade

1967 ◽  
Vol 71 (680) ◽  
pp. 559-565 ◽  
Author(s):  
B. R. Clayton ◽  
B. S. Massey
Keyword(s):  
Reynolds Numbers ◽  
Boundary Layer Separation ◽  
Flow Visualisation ◽  
Bubble Flow ◽  
Hydrogen Bubble ◽  
General Behaviour ◽  
Low Reynolds Numbers ◽  
Separation Results ◽  
Visualisation Technique

SummaryThe pattern of flow at low Reynolds Numbers about an aerofoil in a cascade has been illustrated by the hydrogen-bubble flow-visualisation technique. The method has also been adapted tor the accurate experimental determination of the position of boundary-layer separation. Results of the investigation are presented graphically together with photographs showing the general behaviour of the flow in the wake.

Smoke-wire flow visualization of the near-wake region behind a circular disc at low Reynolds numbers

1994 ◽  
Vol 17 (4) ◽  
pp. 259-266 ◽  
Author(s):  
R. F. Huang ◽  
C. F. Chen ◽  
C. L. Lin ◽  
G. M. Bear
Keyword(s):  
Flow Visualization ◽  
Reynolds Numbers ◽  
Circular Disc ◽  
Wake Region ◽  
Near Wake ◽  
Low Reynolds Numbers ◽  
Low Reynolds

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.

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