NASA NTRS · 19890011579
The 3-D Euler and Navier-Stokes calculations for aircraft components
Abstract
An explicit multistage Runge-Kutta type of time-stepping scheme is used for solving transonic flow past a transport type wing/fuselage configuration. Solutions for both Euler and Navier-Stokes equations are obtained for quantitative assessment of boundary layer interaction effects. The viscous solutions are obtained on both a medium resolution grid of approximately 270,000 points and a find grid of 460,000 points to assess the effects of grid density on the solution. Computed pressure distributions are compared with the experimental data.
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Vatsa, Veer N., Wedan, Bruce W., Turkel, Eli. 1989-03-01. The 3-D Euler and Navier-Stokes calculations for aircraft components. https://ntrs.nasa.gov/citations/19890011579
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