Geodesic
Numerical study of the viscous hypersonic flow over a blunt delta wing
Žurnal vyčislitelʹnoj matematiki i matematičeskoj fiziki, Tome 49 (2009) no. 9, pp. 1697-1707

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A previously developed two-dimensional Navier–Stokes solver is extended to three dimensions. The hypersonic steady flow of an perfect gas (with a constant adiabatic index) over a delta wing with a spherical nose and a cylindrical leading edge is computed as an example. The characteristic features of the flow are analyzed. Pressure, heat flux, and friction coefficient distributions are computed in the shock layer and on the wing surface. The results are compared with available numerical and experimental data. 
@article{ZVMMF_2009_49_9_a15,
     author = {A. B. Gorshkov},
     title = {Numerical study of the viscous hypersonic flow over a~blunt delta wing},
     journal = {\v{Z}urnal vy\v{c}islitelʹnoj matematiki i matemati\v{c}eskoj fiziki},
     pages = {1697--1707},
     publisher = {mathdoc},
     volume = {49},
     number = {9},
     year = {2009},
     language = {ru},
     url = {http://geodesic.mathdoc.fr/item/ZVMMF_2009_49_9_a15/}
}
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A. B. Gorshkov. Numerical study of the viscous hypersonic flow over a blunt delta wing. Žurnal vyčislitelʹnoj matematiki i matematičeskoj fiziki, Tome 49 (2009) no. 9, pp. 1697-1707. http://geodesic.mathdoc.fr/item/ZVMMF_2009_49_9_a15/