Flow separation in the lee side of transverse dunes: A numerical investigation

Geomorphology ◽  
2006 ◽  
Vol 81 (1-2) ◽  
pp. 207-216 ◽  
Author(s):  
Volker Schatz ◽  
Hans J. Herrmann
Keyword(s):  
Numerical Investigation ◽  
Flow Separation ◽  
Transverse Dunes

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

2016 ◽  
Vol 33 (3) ◽  
Author(s):  
Lei Shi ◽  
Xiaowei Liu ◽  
Guoqiang He ◽  
Fei Qin ◽  
Xianggeng Wei ◽  
...  
Keyword(s):  
Numerical Integration ◽  
Numerical Investigation ◽  
Flow Separation ◽  
Static Condition ◽  
Combined Cycle ◽  
Variable Geometry ◽  
Overall Performance ◽  
Negative Impacts

AbstractNumerical integration simulations were performed on a ready-made central strut-based rocket-based combined-cycle (RBCC) engine operating in the ejector mode during the takeoff regime. The effective principles of various cowl lip positions and shapes on the inlet operation and the overall performance of the entire engine were investigated in detail. Under the static condition, reverse cowl lip rotation in a certain range was found to contribute comprehensive improvement to the RBCC inlet and the entire engine. However, the reverse rotation of the cowl lip contributed very little enhancement of the RBCC inlet under the low subsonic flight regime and induced extremely negative impacts in the high subsonic flight regime, especially in terms of a significant increase in the drag of the inlet. Changes to the cowl lip shape provided little improvement to the overall performance of the RBCC engine, merely shifting the location of the leeward area inside the RBCC inlet, as well as the flow separation and eddy, but not relieving or eliminating those phenomena. The results of this study indicate that proper cowl lip rotation offers an efficient variable geometry scheme for a RBCC inlet in the takeoff regime.

scholarly journals COMPARISON OF AERODYNAMICS CHARACTERISTICS OF NACA 0015 & NACA 4415 AEROFOIL BLADE

2017 ◽  
Vol 5 (11) ◽  
pp. 187-197
Author(s):  
Rubel R. I. ◽  
Uddin ◽  
Islam ◽  
Rokunuzzaman
Keyword(s):  
Numerical Investigation ◽  
Turbine Blade ◽  
Flow Separation ◽  
Aircraft Wing ◽  
Fluid Medium ◽  
Aerodynamic Shape ◽  
Velocity Contour ◽  
And Performance ◽  
Naca 0015

NACA 0015 and NACA 4415 aerofoil are most common four digits and broadly used aerodynamic shape. Both of the shapes are extensively used for various kind of applications including turbine blade, aircraft wing and so on. NACA 0015 is symmetrical and NACA 4415 is unsymmetrical in shape. Consequently, they have big one-of-a-kind in aerodynamic traits at the side of widespread differences of their utility and performance. Both of them undergo the same fluid principle while applied in any fluid medium giving dissimilar outcomes in aerodynamics behavior. On this work, experimental and numerical investigation of each NACA 0015 and NACA 4415 is done to decide their performance. For this purpose, aerofoil section is tested for a prevalence range attack of angle (AOA). The study addresses the performance of NACA 0015 and NACA 4415 and evaluates the dynamics of flow separation, lift, drag, pressure and velocity contour and so on.

Numerical investigation of flow separation ahead of a step

1979 ◽  
Vol 14 (5) ◽  
pp. 693-699
Author(s):  
V. I. Myshenkov
Keyword(s):  
Numerical Investigation ◽  
Flow Separation

scholarly journals A numerical investigation on the vortex formation and flow separation of the oscillatory flow in jet pumps

2015 ◽  
Vol 137 (4) ◽  
pp. 1722-1731 ◽  
Author(s):  
Joris P. Oosterhuis ◽  
Simon Bühler ◽  
Theo H. van der Meer ◽  
Douglas Wilcox
Keyword(s):  
Numerical Investigation ◽  
Flow Separation ◽  
Oscillatory Flow ◽  
Vortex Formation ◽  
Jet Pumps

scholarly journals Comparison of Aerodynamics Characteristics of NACA 0015 & NACA 4415

2016 ◽  
Author(s):  
Robiul Islam Rubel ◽  
Md. K. Uddin ◽  
Md. Zahidul Islam ◽  
Md. Rokunuzzaman
Keyword(s):  
Drag Reduction ◽  
Numerical Investigation ◽  
Turbine Blade ◽  
Flow Separation ◽  
Aircraft Wing ◽  
Fluid Medium ◽  
Velocity Contour ◽  
Lift Enhancement ◽  
And Performance ◽  
Naca 0015

NACA 0015 and NACA 4415 aerofoil are most common four digits and broadly used aerodynamic shape. Both of the shapes are extensively used for various kind of applications including turbine blade, aircraft wing and so on. NACA 0015 is symmetrical and NACA 4415 is unsymmetrical in shape. Consequently, they have big one-of-a-kind in aerodynamic traits at the side of widespread differences of their utility and performance. Both of them undergo the same fluid principle while applied in any fluid medium giving dissimilar outcomes in aerodynamics behavior. On this work, experimental and numerical investigation of each NACA 0015 and NACA 4415 is done to decide their performance. For this purpose, aerofoil section is tested for a prevalence range attack of angle (AOA). The study addresses the performance of NACA 0015 and NACA 4415 and evaluates the dynamics of flow separation, lift, drag, pressure and velocity contour and so on. This additionally enables to layout new optimistic aerofoil, which is critical to enhance the efficiency and performance of an aircraft in terms of lift enhancement and drag reduction.

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