Existence of piecewise smooth attached-shock self-similar solutions is established for supersonic Chaplygin gas flow past a conical wing with Λ-shaped cross sections.
Anderson, Jr.,Fundamentals of Aerodynamics, McGraw-Hill series in aeronautical and aerospace engineering, Sixth edition, McGraw-Hill Education, New York
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Supersonic flow of a Chaplygin gas past a conical wing with $\Lambda$-shaped cross sections
Existence of piecewise smooth attached-shock self-similar solutions is established for supersonic Chaplygin gas flow past a conical wing with Λ-shaped cross sections.