薄い二次元物體の前後端より生ずる衝撃波の形状について

概要

論文の詳細を見る
Shapes of shock waves issuing from both pointed ends of two-dimensional slender body are studied in relation to the body form. In the present paper, the entropy change behind a curved shock is ignored under the assumption of small deflected angle θ. Therefore, Mach lines become straight with flow variables constant along them. Fundamental equations which connect the shape (x, y) of the shock with that (ξ,η) of the body are given in (1) and (2). They are solved by expanding the slope tan β of the shock and Mach angle μ behind it into power series of θ and neglecting smaller terms than θ^3. The results are given in (5) and (6) for bow and rear shocks, respectively. The coefficients of the series are obtained from Rankine-Hugoniot's relation on oblique shock and Prandtl-Meyer's solution on adiabatic supersonic flow. Then, asymplotic form of the solution at large distances is studied and it is found that shock waves become parabolic as are shown in (13) and (14), and that the distance between bow and rear shocks increases as the square root of the distance from a-axis. The curvature K_0 of the shock at the nose is also obtained and compared with the strict solution by C. C. Lin and G. B. Rubinov. The shape of bow shock of a circular are wing is calculated as an example in the last section.
宇宙航空研究開発機構の論文
1951-03-16