To the Theory of Hypersonic Flow around a Thin Delta Finite-Swept Wing at a Large Attack Angle

The paper reviews the most important results in solving the problem of a hypersonic flow around a thin finite-swept delta wing at large angles of attack close to the right angle obtained by the author using the thin shock-layer method. The classification of all the basic modes and schemes of the flows realized in the proposed theory is supplemented by the two main similarity parameters. A composite solution, which adequately represents the disturbed flow both in the main shock-layer part and in the near-wall entropy layer, is obtained.