A B C D E F G H I J K L M N O P Q R S T U V W X Y Z All
C M, Rakesh
- A study on performance of surface modified NACA 2412 airfoil at various Reynolds number and angle of attacks
Authors
1 School of Mechanical Engineering, REVA University, Bangalore, IN
2 Nitte Meenakshi Institute of Technology, Bangalore, IN
Source
Journal of Mines, Metals and Fuels, Vol 69, No 12A (2021), Pagination: 269-275Abstract
In the present investigation, aerodynamic performance study of NACA 2412 airfoil with surface modifications for the enhanced optimized aerodynamic characteristics is carried out. Three airfoils were built by introducing the cut at different locations. The present work is a computational analysis of the effect of inward cut on the lower surface of airfoil at 25%, 50%, and 75% chord length. The study parameters include flow separation (or stall), lift, drag, and angle of attack. The model is developed in Ansys design modeler and meshed in ICEMCFD. All three meshed models are simulated at 0o, 40o, 80o, 120o and 16o angle of attacks (AoA) at 60000 and 100000 (1 lakh) Reynolds number. The post processing revealed that, the increase in AoA resulted in increase in lift co-efficient (CL) for all three airfoils at both Reynolds number. The lift coefficient started increasing as the position of cut moved towards the trailing edge. The flow started separating after 12o AoA. It was found that, the airfoil with inward cut at 75% of chord length resulted in attaining highest lift co-efficient when compared to other two airfoils.Keywords
NACA, airfoil, angle of attack, Reynolds number.References
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- Design and Analysis of Wing Root Fitting of a Medium Fighter Aircraft Made of B4C Reinforced Al7075 Alloy
Authors
1 School of Mechanical Engineering, REVA University, Bangalore 560064,Karnataka, India., IN
2 Assistant Professor, School of Mechanical Engineering, REVA University, Bangalore., IN
Source
Journal of Mines, Metals and Fuels, Vol 70, No 10A (2022), Pagination: 318-323Abstract
In the present work, an attempt has been made to synthesize metal matrix composite using Al7075 as matrix material with B4C particles as reinforcement using liquid metallurgy technique in particular stir casting process. Microstructural characterization was carried out for the above prepared composites by taking specimens from central portion of the casting by microstructural studies and SEM analysis. Tensile, shear, compression and bending properties of the prepared composite were studied before and after addition of Al7075 particulates to note the extent of improvement. Microstructural characterization of the composites has revealed fairly uniform distribution of B4C particulates and some amount of grain refinement in the specimens.
The design and analysis of wing root fitting of on medium fighter aircraft carried out using CATIA V5 and ANSYS workbench software. Finite element method is used for the stress analysis. Calculation of equivalent stress, shear stress and total deformation will be considered under this study.
Keywords
A17075, SEM, B4C, CATIA V5, ANSYS Workbench Software, Reinforced, Wing Root Fitting, Aircraft etc.References
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