Experimental investigation of shock wave patterns over a NACA 0012 profile

2015 ◽  
Author(s):  
Layra Mendonça ◽  
Ana Cristina Avelar ◽  
João Batista Pessoa Falcão Filho ◽  
Cayo Prado Fernandes Francisco
Keyword(s):  
Shock Wave ◽  
Experimental Investigation ◽  
Wave Patterns ◽  
Naca 0012

Experimental investigation on the shock-wave load attenuation by geometrical means

Shock Waves ◽  
2009 ◽  
Vol 20 (1) ◽  
pp. 29-40 ◽  
Author(s):  
Shachar Berger ◽  
Oren Sadot ◽  
Gabi Ben-Dor
Keyword(s):  
Shock Wave ◽  
Experimental Investigation ◽  
Wave Load

Aerodynamic Investigation of Double Surface Airfoil

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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