Aerodynamic Investigation on Efficient Inflight Transition of a Propeller from Propulsion to Regeneration Mode

This study describes an effectively analytic methodology to investigate the aerodynamic performance of H vertical axis wind turbine (H-VAWT). An in-house code based on double multiple stream tube theory (DMST) coupled with dynamic stall and wake correction is implemented to estimate the power coefficient. Design optimization of airfoil shape is conducted to study the influences of the dynamic stall and turbulent wakes. Airfoil shape is universally investigated by using the Class/Shape function transformation method. The airfoil study shows that the upper curve tends to be less convex than the lower curve in order to extract more energy of the wind upstream and generate less drag of the blade downstream. The optimal results show that the power coefficient increases by 6.5% with the new airfoil shape.

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Aerodynamic Investigation of a Composite Low-Speed Fan for UHBR Application

10.1115/1.0003148v ◽

2021 ◽

Author(s):

Martin Rodrigues ◽

Laurent Soulat ◽

Benoit Paoletti ◽

Xavier Ottavy ◽

Brandstetter Brandstetter

Keyword(s):

Low Speed ◽

Aerodynamic Investigation

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Aerodynamic Investigation of Double Surface Airfoil

ACS Journal for Science and Engineering ◽

10.34293/acsjse.v1i2.13 ◽

2021 ◽

Vol 1 (2) ◽

pp. 41-46

Author(s):

Siva J ◽

Suresh C ◽

Paramaguru V

Keyword(s):

Experimental Investigation ◽

Flow Separation ◽

Research Work ◽

Aerodynamic Performance ◽

Aircraft Industry ◽

Aerodynamic Efficiency ◽

Flight Vehicles ◽

Double Surface ◽

Naca 0012 ◽

Aerodynamic Investigation

Aircraft industry has been deeply concerned about reduction of drag by reducing flow separation and improving the aerodynamic efficiency of flight vehicles, particularly in commercial and military market by adopting various methods. Reduction of flow separation is a concept by which we can increase aerodynamic efficiency. The purpose of the project is to perform an experimental investigation on aerodynamic performance of NACA 0012 airfoil model with and without splits. It is evident from this research work that the airfoil model with split possesses greater aerodynamic performance by producing lesser overall drag. This is due to the delay in flow separation from the surface.

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Aerodynamic investigation of the shock train in a scramjet with the effects of backpressure and divergent angles

Heat Transfer ◽

10.1002/htj.21856 ◽

2020 ◽

Vol 49 (8) ◽

pp. 4857-4869

Author(s):

Santhosh K. Gugulothu

Keyword(s):

Shock Train ◽

Aerodynamic Investigation

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Aerodynamic Investigation of a Passive Secondary Jet Exciting a Separation Bubble for a Blunt Flat Plate

Volume 1: Symposia ◽

10.1115/ajkfluids2015-15065 ◽

2015 ◽

Author(s):

Christian Helcig ◽

Stefan aus der Wiesche ◽

Stephan Uhkoetter

Keyword(s):

Boundary Layer ◽

Laser Doppler Anemometry ◽

Separation Bubble ◽

Flow Characteristics ◽

Numerical Procedure ◽

Large Eddy Simulations ◽

Reattachment Length ◽

Large Eddy ◽

Low Speed Wind Tunnel ◽

Aerodynamic Investigation

The aim of this study is to examine the influence of passive jets interacting with the separation region of the flow around a blunt plate. Experimental and numerical analysis are used to measure the velocity within the separation and reattachment region of the blunt plate with different passive jet configurations. A blunt plate was placed in a low speed wind tunnel to conduct Laser-Doppler anemometry (LDA) measurements at Re = 2.06 × 104. For the numerical procedure a dynamical sub-grid model for Large Eddy Simulations (LES) was used. For all configurations the flow characteristics such as the reattachment length were determined to characterize the boundary layer. The passive jets showed a strong influence by interacting with the boundary layer of the blunt plate.

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