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- [2] THE FLOW OVER A FLAT PLATE WITH A SMALL ANGLE OF ATTACK AT MACH NUMBER-1JOURNAL OF THE AERONAUTICAL SCIENCES, 1954, 21 (04): : 261 - 274GUDERLEY, G
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- [4] The effects of Mach number on the flow separation control of airfoil with a small plate near the leading edgeCOMPUTERS & FLUIDS, 2017, 156 : 274 - 282Zhou, YangweiHou, LongfengHuang, Diangui
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- [6] SOLUTION TO THE FLOW ABOUT A 2-DIMENSIONAL FLAT PLATE AT INFINITE MACH NUMBERJOURNAL OF THE AEROSPACE SCIENCES, 1960, 27 (01): : 68 - 68CHUBB, DL
- [7] Leading-edge bluntness effects in hypervelocity flat plate flowPHYSICS OF FLUIDS, 2020, 32 (04)Mallinson, S. G.Mudford, N. R.Gai, S. L.
- [8] ON THE VISCOUS FLOW AROUND THE LEADING EDGE OF A FLAT PLATEJOURNAL OF THE AEROSPACE SCIENCES, 1959, 26 (07): : 453 - 454BOLEY, BAFRIEDMAN, MB
- [9] FLOW FIELD AHEAD OF LEADING EDGE OF A FLAT PLATEBULLETIN OF THE AMERICAN PHYSICAL SOCIETY, 1972, 17 (11): : 1109 - 1109CHENG, DY
- [10] HYPERSONIC FLOW NEAR THE LEADING EDGE OF A FLAT PLATEPHYSICS OF FLUIDS, 1960, 3 (01) : 140 - 141NAGAMATSU, HTLI, TY