Computational and Theoretical Fluid Dynamics Division, Council of Scientific and Industrial Research, National Aerospace Laboratories, Bangalore – 560017, India
Unsteady Reynolds-averaged Navier-Stokes (RANS) computations are presented for subsonic and transonic flow past a plunging NACA 64A010 aerofoil. The Implicit RANS solver used for obtaining the time-accurate solution is based on finite volume nodal point spatial discretization scheme with dual time stepping. Results for the subsonic and transonic cases compare well with the experimental data, thus demonstrating the capability of the solver to provide useful unsteady pressure data for aeroelastic analysis.
Kumar, K. S., & Sajjan, S. V. (2013). Numerical Computation of Unsteady Compressible Flow past a Plunging Aerofoil. Journal of Applied Fluid Mechanics, 5(4), 131-138. doi: 10.36884/jafm.5.04.19471
MLA
K. S. Kumar; S. V. Sajjan. "Numerical Computation of Unsteady Compressible Flow past a Plunging Aerofoil". Journal of Applied Fluid Mechanics, 5, 4, 2013, 131-138. doi: 10.36884/jafm.5.04.19471
HARVARD
Kumar, K. S., Sajjan, S. V. (2013). 'Numerical Computation of Unsteady Compressible Flow past a Plunging Aerofoil', Journal of Applied Fluid Mechanics, 5(4), pp. 131-138. doi: 10.36884/jafm.5.04.19471
VANCOUVER
Kumar, K. S., Sajjan, S. V. Numerical Computation of Unsteady Compressible Flow past a Plunging Aerofoil. Journal of Applied Fluid Mechanics, 2013; 5(4): 131-138. doi: 10.36884/jafm.5.04.19471
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