scholarly journals Comparative Study of Forward Wingtip Fence and Rearward Wingtip Fence on Wing Airfoil Eppler E562

2020 ◽  
Vol 5 (1) ◽  
pp. 25
Author(s):  
Setyo Hariyadi ◽  
Sutardi Sutardi ◽  
Wawan Aries Widodo ◽  
Bambang Juni Pitoyo
Keyword(s):  
Reynolds Number ◽  
Fluid Flow ◽  
Comparative Study ◽  
Pressure Gradient ◽  
Fuel Consumption ◽  
Leading Edge ◽  
Aircraft Design ◽  
Aircraft Performance ◽  
Wing Geometry ◽  
Wing Airfoil

The perfect wing is a dream that many airplanes has manufactured have been striving to achieve since the beginning of the airplane design. There are some aspect that most influence in aircraft design lift, drag, thrust, and weight. The combination of these aspects leads to a decrease in fuel consumption, which reduces pollution in our atmosphere and increase in economic revenue. One way to improve aircraft performance is to modify the tip of the wing geometry, which has become a common sight on today’s airplanes. With computational programs, the effects on drag due to wingtip devices can be previewed. This research was done numerically by using turbulence model k-ω SST. Reynolds number in this research was 2,34 x 10 4 with angle of attacks are 0o, 2o, 4o, 6o, 8o, 10o, 12o, 15o, 17o and 19o. The model specimen is wing airfoil Eppler 562 with winglets. Two types of wingtips are used: forward and rearward wingtip fence. From this study, it was found that wingtip fence reduced the strength of vorticity magnitude on the x axis compared to plain wings. The leakage of fluid flow effect at the leading edge corner of the wingtip, giving pressure gradient and slightly shifting towards the trailing edge. this occurs in the plain wing and rearward wingtip fence but does not occur in the forward wingtip fence..

The Comparative Study Between Swirl and Impingement of Mist/Air Cooling on Blade Leading Edge

2015 ◽  
Author(s):  
Yuting Jiang ◽  
Qun Zheng ◽  
Bo Liu ◽  
Jie Gao ◽  
Hai Zhang
Keyword(s):  
Heat Transfer ◽  
Reynolds Number ◽  
Comparative Study ◽  
Pressure Loss ◽  
Leading Edge ◽  
Swirl Flow ◽  
Air Cooling ◽  
Impingement Cooling ◽  
Pressure Loss Coefficient ◽  
Blade Leading Edge

A comparative study of the flow field and heat transfer characteristics between swirl and impingement of mist/air cooling on blade leading edge is carried out to find better cooling configuration for phase transition cooling. The Eulerian-Lagrangian particle tracking technique is used to investigate the mist/air cooling. Comparisons are made between these two cooling forms in such aspects as vortex structure, heat transfer enhancement, pressure loss, and thermal uniformity with and without mist injection. The influences of mist ratio and Reynolds numbers on these parameters are studied in this paper. Results show that the heat transfer is enhanced, pressure loss and the thermal uniformity is improved by the swirl flow created by vortex impingement. The heat transfer performance increases by about 46.2% and 51.9% for impingement and swirl cooling with 8% mist injection, and the pressure loss coefficient increases by 19%. The difference of heat transfer coefficient between swirl and impingement cooling with and without mist injection at high Reynolds number is larger than that at low Reynolds number. In addition, heat transfer non-uniform coefficient of swirl cooling is about 15% lower than impingement cooling.

Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow

2018 ◽  
Author(s):  
Brian M. Holley ◽  
Larry W. Hardin ◽  
Gregory Tillman ◽  
Ray-Sing Lin ◽  
Jongwook Joo
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Pressure Gradient ◽  
Skin Friction ◽  
High Reynolds Number ◽  
Gradient Flow ◽  
Leading Edge ◽  
Adverse Pressure Gradient ◽  
Data Set ◽  
High Reynolds

A combined experimental and analytical modeling effort has been carried out to measure the skin friction response of the boundary layer in high Reynolds number adverse pressure gradient flow. The experiment was conducted in the United Technologies Research Center (UTRC) Acoustic Research Tunnel, an ultra-low freestream turbulence facility capable of laminar boundary layer research. Boundary layer computational fluid dynamics and stability modeling were used to provide pre-test predictions, as well as to aid in interpretation of measured results. Measurements were carried out at chord Reynolds numbers 2–3 × 106, with the model set at multiple incidence angles to establish a range of relevant leading edge pressure gradients. The combination of pressure gradient and flight Reynolds number testing on a thin airfoil has produced a unique data set relevant to propulsion system turbomachinery.

Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow

2020 ◽  
Vol 142 (2) ◽  
Author(s):  
Brian M. Holley ◽  
Larry W. Hardin ◽  
Gregory Tillman ◽  
Ray-Sing Lin ◽  
Jongwook Joo
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Pressure Gradient ◽  
Skin Friction ◽  
High Reynolds Number ◽  
Gradient Flow ◽  
Leading Edge ◽  
Adverse Pressure Gradient ◽  
Data Set ◽  
High Reynolds

Abstract A combined experimental and analytical modeling effort has been carried out to measure the skin friction response of the boundary layer in high Reynolds number adverse pressure gradient flow. The experiment was conducted in the United Technologies Research Center (UTRC) Acoustic Research Tunnel, an ultra-low freestream turbulence facility capable of laminar boundary layer research. Boundary layer computational fluid dynamics and stability modeling were used to provide pre-test predictions, as well as to aid in interpretation of measured results. Measurements were carried out at chord Reynolds numbers 2–3 × 106, with the model set at multiple incidence angles to establish a range of relevant leading edge pressure gradients. The combination of pressure gradient and flight Reynolds number testing on a thin airfoil has produced a unique data set relevant to propulsion system turbomachinery.

scholarly journals STUDI NUMERIK PENGGUNAAN VORTEX GENERATOR PADA WING AIRFOIL NACA 43018

2019 ◽  
Vol 4 (3) ◽  
pp. 67-77
Author(s):  
Setyo Hariyadi Suranto Putro ◽  
Achmad Setiyo Prabowo
Keyword(s):  
Pressure Gradient ◽  
Flat Plate ◽  
Vortex Generator ◽  
Leading Edge ◽  
Adverse Pressure Gradient ◽  
Wing Airfoil

Pesawat terbang merupakan aplikasi ilmu mekanika fluida yang sangat memperhatikan aspek aerodinamika karena berkaitan dengan performa pada penerbangan. Satu hal penting yang harus diperhatikan dalam pendesainan suatu pesawat yaitu pemilihan airfoil dan modifikasinya. Modifikasi airfoil dilakukan untuk menunda separasi aliran dan meningkatkan performa airfoil, salah satunya dengan vortex generator. Modifikasi pada airfoil dilakukan untuk meningkatkan performansi dari airfoil. Hal ini dapat diindikasikan dengan tertundanya separasi aliran yang melintasi permukaan atas dari airfoil. Dengan tertundanya separasi ini maka gaya lift akan semakin besar dan gaya drag akan semakin kecil. Penelitian sebelumnya menunjukkan bahwa penambahan vortex generator pada permukaan atas airfoil dapat menunda terjadinya separasi aliran. Hal ini disebabkan aliran lebih tahan melawan gaya gesek dan adverse pressure gradient. Topik yang dikaji dalam penelitian ini adalah aliran melintasi airfoil NACA 43018 dengan penambahan vortex generator. Airfoil NACA 43018 digunakan pada sayap pesawat terbang ATR 72. Tujuan penelitian ini adalah untuk membandingkan karakteristik aliran fluida dengan dan tanpa penambahan vortex generator. Profil vortex generator yang digunakan adalah flat plate vortex generator dengan konfigurasi straight dan ditempatkan pada x/c = 10% dan 20% arah chord line dari leading edge. Variasi yang digunakan adalah bilangan Reynolds (Re) dan sudut serang (α) pada airfoil. Kecepatan freestream yang digunakan yaitu kecepatan 12 m/s atau Re = 7,65 x 105 dan kecepatan 17 m/s atau Re = 9 x 105, dan pada sudut serang (α) 0o, 3o, 6o, 9o, 12o, 15o, 19o, dan 20o. Parameter yang dievaluasi meliputi koefisien tekanan (Cp), profil kecepatan, gaya lift, gaya drag, dan rasio CL/CD. Hasil penelitian ini menunjukkan bahwa terjadi peningkatan performansi dari airfoil NACA 43018 dengan penambahan vortex generator dibandingkan dengan tanpa vortex generator. Adanya vortex generator, dapat menunda terjadinya separasi. Dengan penambahan vortex generator terjadi peningkatan gaya lift sekitar 5% dan menaikkan gaya drag sekitar 1,5%. Rasio CL/CD meningkat sekitar 5 %.

scholarly journals Investigasi Perbandingan Posisi Rectangular Flat Plate Vortex Generator dengan Posisi Straight pada Wing Airfoil NACA 43018

2018 ◽  
Vol 3 (3) ◽  
pp. 36-43
Author(s):  
Setyo Hariyadi S.P ◽  
Wawan Aries Widodo ◽  
Bambang Junipitoyo ◽  
Wiwid Suryono ◽  
Supriadi Supriadi
Keyword(s):  
Pressure Gradient ◽  
Flat Plate ◽  
Vortex Generator ◽  
Leading Edge ◽  
Adverse Pressure Gradient ◽  
Wing Airfoil

Pesawat terbang merupakan aplikasi ilmu mekanika fluida yang sangat memperhatikan aspek aerodinamika karena berkaitan dengan performa pada penerbangan. Satu hal penting yang harus diperhatikan dalam pendesainan suatu pesawat yaitu pemilihan airfoil dan modifikasinya. Modifikasi airfoil dilakukan untuk menunda separasi aliran dan meningkatkan performa airfoil, salah satunya dengan vortex generator. Modifikasi pada airfoil dilakukan untuk meningkatkan performansi dari airfoil. Hal ini dapat diindikasikan dengan tertundanya separasi aliran yang melintasi permukaan atas dari airfoil. Dengan tertundanya separasi ini maka gaya lift akan semakin besar dan gaya drag akan semakin kecil. Penelitian sebelumnya menunjukkan bahwa penambahan vortex generator pada permukaan atas airfoil dapat menunda terjadinya separasi aliran. Hal ini disebabkan aliran lebih tahan melawan gaya gesek dan adverse pressure gradient. Topik yang dikaji dalam penelitian ini adalah aliran melintasi airfoil NACA 43018 dengan penambahan vortex generator. Airfoil NACA 43018 digunakan pada sayap pesawat terbang ATR 72. Tujuan penelitian ini adalah untuk membandingkan karakteristik aliran fluida dengan dan tanpa penambahan vortex generator. Profil vortex generator yang digunakan adalah rectangular flat plate vortex generator dengan konfigurasi straight dan ditempatkan pada x/c = 10% dan 20% arah chord line dari leading edge. Variasi yang digunakan adalah bilangan Reynolds (Re) dan sudut serang (α) pada airfoil. Kecepatan freestream yang digunakan yaitu kecepatan 12 m/s atau Re = 7,65 x 105 dan kecepatan 17 m/s atau Re = 9 x 105, dan pada sudut serang (α) 0o, 3o, 6o, 9o, 12o, 15o, 19o, dan 20o. Parameter yang dievaluasi meliputi koefisien tekanan (Cp), profil kecepatan, lift, drag, dan rasio CL/CD. Hasil penelitian ini menunjukkan bahwa terjadi peningkatan performansi dari airfoil NACA 43018 dengan penambahan vortex generator dibandingkan dengan tanpa vortex generator. Adanya vortex generator, dapat menunda terjadinya separasi. Dengan penambahan vortex generator terjadi peningkatan lift sekitar 5% dan menaikkan drag sekitar 1,5%. Rasio CL/CD meningkat sekitar 5 %.

Characteristics of a separated flow past a semicircular leading-edge airfoil model under different imposed pressure gradient

2021 ◽  
pp. 095441002110212
Author(s):  
K Anand ◽  
KT Ganesh
Keyword(s):  
Boundary Layer ◽  
Particle Image Velocimetry ◽  
Pressure Gradient ◽  
Particle Image ◽  
Separation Bubble ◽  
Separated Flow ◽  
Leading Edge ◽  
Field Measurements ◽  
Bench Mark ◽  
Image Velocimetry

The effect of pressure gradient on a separated boundary layer past the leading edge of an airfoil model is studied experimentally using electronically scanned pressure (ESP) and particle image velocimetry (PIV) for a Reynolds number ( Re) of 25,000, based on leading-edge diameter ( D). The features of the boundary layer in the region of separation and its development past the reattachment location are examined for three cases of β (−30°, 0°, and +30°). The bubble parameters such as the onset of separation and transition and the reattachment location are identified from the averaged data obtained from pressure and velocity measurements. Surface pressure measurements obtained from ESP show a surge in wall static pressure for β = −30° (flap deflected up), while it goes down for β = +30° (flap deflected down) compared to the fundamental case, β = 0°. Particle image velocimetry results show that the roll up of the shear layer past the onset of separation is early for β = +30°, owing to higher amplification of background disturbances compared to β = 0° and −30°. Downstream to transition location, the instantaneous field measurements reveal a stretched, disoriented, and at instances bigger vortices for β = +30°, whereas a regular, periodically shed vortices, keeping their identity past the reattachment location, is observed for β = 0° and −30°. Above all, this study presents a new insight on the features of a separation bubble receiving a disturbance from the downstream end of the model, and these results may serve as a bench mark for future studies over an airfoil under similar environment.

Instability of a gravity current within a soap film

2014 ◽  
Vol 753 ◽  
Author(s):  
Raymond E. Goldstein ◽  
Herbert E. Huppert ◽  
H. Keith Moffatt ◽  
Adriana I. Pesci
Keyword(s):  
Fluid Flow ◽  
Gravity Current ◽  
Leading Edge ◽  
Soap Film ◽  
Plateau Border ◽  
Dynamic Variations ◽  
Characteristic Wavelength ◽  
Overall Stability ◽  
Stability Regime ◽  
Good Agreement

AbstractOne of the simplest geometries in which to study fluid flow between two soap films connected by a Plateau border is provided by a catenoid with a secondary film at its narrowest point. Dynamic variations in the spacing between the two rings supporting the catenoid lead to fluid flow between the primary and secondary films. When the rings are moved apart, while keeping their spacing within the overall stability regime of the films, after a rapid thickening of the secondary film the excess fluid in it starts to drain into the sloped primary film through the Plateau border at which they meet. This influx of fluid is accommodated by a local thickening of the primary film. Experiments described here show that after this drainage begins the leading edge of the gravity current becomes linearly unstable to a finite-wavelength fingering instability. A theoretical model based on lubrication theory is used to explain the mechanism of this instability. The predicted characteristic wavelength of the instability is shown to be in good agreement with experimental results. Since the gravity current advances into a film of finite, albeit microscopic, thickness this situation is one in which the regularization often invoked to address singularities at the nose of a thin film is physically justified.

Rotating elliptic cylinders in a viscous fluid at rest or in a parallel stream

1977 ◽  
Vol 79 (1) ◽  
pp. 127-156 ◽  
Author(s):  
Hans J. Lugt ◽  
Samuel Ohring
Keyword(s):  
Reynolds Number ◽  
Fluid Flow ◽  
Numerical Solutions ◽  
Elliptic Cylinder ◽  
The Body ◽  
Oscillatory Behaviour ◽  
Incompressible Fluid Flow ◽  
Transient Period ◽  
Parallel Stream ◽  
Rotating Bodies

Numerical solutions are presented for laminar incompressible fluid flow past a rotating thin elliptic cylinder either in a medium at rest at infinity or in a parallel stream. The transient period from the abrupt start of the body to some later time (at which the flow may be steady or periodic) is studied by means of streamlines and equi-vorticity lines and by means of drag, lift and moment coefficients. For purely rotating cylinders oscillatory behaviour from a certain Reynolds number on is observed and explained. Rotating bodies in a parallel stream are studied for two cases: (i) when the vortex developing at the retreating edge of the thin ellipse is in front of the edge and (ii) when it is behind the edge.

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