Application of computational fluid dynamics to a monoplane fixed-wing missile with elliptic cross sections

Original publisher: Aberdeen Proving Ground, MD: Army Research Laboratory, [2005] OCLC Number: (OCoLC)710818237 Subject: Guided missiles -- Aerodynamics -- Models. Excerpt: ... Figure 4. Axial locations for experimental data. Figure 5. Circumferential locations of experimental data points. 4.1 Qualitative Results Visualization of pressure on the missile surface appears to be the same for both the hexahedral and tetrahedral solutions, as seen in figure 6. However, Mach and Pressure contours show the flow field characteristics to be more defined in the solutions for the hexahedral mesh. The longitudinal Mach contours for the y = 0 pitch plane depicted in figure 7 show this to be 7