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Rinku Mukherjee
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Rinku Mukherjee
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Rinku Mukherjee
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Rinku, Mukherjee
Mukherjee, R.
Mukherjee, Rinku
Mukherjeey, Rinku
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2 results
Now showing 1 - 2 of 2
- PublicationA study of the unsteady aerodynamics of a wing at high angles of attack using decambering to model separated flow(01-08-2018)
;Samuel, B. AntonyAn Unsteady Vortex Lattice Method is developed and validated. It is coupled with a decambering methodology to account for viscous effects on the aerodynamic coefficients. Two additional methodologies to select a unique solution when multiple solutions arise have been proposed. The transient nature of the aerodynamic loads of a suddenly moving wing at different angles of attack is examined. Sudden jumps are observed in the CL(t) at post-stall angles of attack. The jumps are followed by the presence of asymmetric solutions, which then decline with time and a change in the solution state. Higher angles of attack see an increasing number of jumps. - PublicationExperimental and computational investigations of aerodynamic characteristics of a finite rectangular wing-in-ground effect(01-04-2023)
;Shirsath, Ravindra A.Wind tunnel experiments are carried out on a 3D wing-in-ground effect at pre- and post-stall angles of attack at a relatively low Reynolds number, Re ≈ 8.8 × 104. The rectangular wing, aspect ratio, AR = 6.4 used in the present work has a symmetric airfoil section, NACA0012 and is studied at different ranges of ground proximity and also compared to a wing of cambered airfoil section, NACA4415 not in ground proximity. Unsteady and time-averaged six-component aerodynamic characteristics, coefficients of Lift, Drag, Side forces, Pitch, Roll, Yaw moments at several angles of attack in the range – 8° < α < 18° are reported. Aerodynamic efficiency and drag polars are studied in lieu of ground proximity at several angles of attack. Effect of ground proximity on the occurrence of stall and (Formula presented.) is studied. Numerical calculations using steady-state CFD are also made for quantitative comparison. The effect of ground proximity on span-wise pressure distribution and induced velocity in the vicinity of the wing is also discussed in detail.