Affiliation:
1. Noorul Islam Centre for higher education
2. Parul University
Abstract
Abstract
The objective of this paper is to predict the suitable injection angle for co flow jet (CFJ) method to obtain the optimum aerodynamic performance. This can be achieved through numerical study of NACA 2412 aerofoil with four different injection angles with free stream Mach number of 0.058 using k epsilon equations. The Primary aim of this paper is to analyses the injection flow angle over the CFJ method for effective control of boundary layer. This paper concluded that the optimum injection angle of CFJ method is 60 degree which improved the stalling angle of attack (AOA) by 25% and drag reduction of 40% as compared to regular CFJ method. This ingenious method can be used for regular co flow jet method to improve the aerodynamic performance from commercial aircraft to fighter aircrafts.
Publisher
Research Square Platform LLC
Reference21 articles.
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