2021
DOI: 10.1108/aeat-06-2020-0122
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Computational analysis to enhance the compressible flow over an aerofoil surface

Abstract: Purpose Since the inception of aerospace engineering, reducing drag is of eternal importance. Over the years, researchers have been trying to improve the aerodynamics of National Advisory Committee for Aeronautics (NACA) aerofoils in many ways. It is proved that smooth-surfaced NACA 0012 aerofoil produces more drag in compressible flow. Recent research on shark-skin pattern warrants a feasible solution to many fluid-engineering problems. Several attempts were made by many researchers to implement the idea of s… Show more

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Cited by 5 publications
(2 citation statements)
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“…The gauge pressure was calculated with the use of below mentioned formulae. [20] where P 0 -Total pressure (101325 pa), P -Static pressure, γ -Gas constant (1.4), M-Mach number (0.8). Spalart Allmarasa one equation model opted for its effectiveness in external fluid flow investigations.…”
Section: Computational Analysismentioning
confidence: 99%
“…The gauge pressure was calculated with the use of below mentioned formulae. [20] where P 0 -Total pressure (101325 pa), P -Static pressure, γ -Gas constant (1.4), M-Mach number (0.8). Spalart Allmarasa one equation model opted for its effectiveness in external fluid flow investigations.…”
Section: Computational Analysismentioning
confidence: 99%
“…Even this turbulent boundary layer is less resistant to separation, leading to increased skin friction drag compared to a purely laminar flow scenario. The riblet mechanism can reduce 8 to 10% of the total skin friction drag [14][15][16][17][18][19]. The effectiveness of drag reduction using riblet surfaces is impacted by a range of elements, encompassing factors like riblet geometry, Reynolds number, surface roughness, riblet alignment, interaction with the boundary layer, and many more.…”
Section: Introductionmentioning
confidence: 99%