This paper presents an approximate solution for the hypersonic inviscid flow around spherically blunted bodies flying at small angles of attack. The procedure given by LI & GEIGER for the special case of symmetric flow with a spherical shock wave is extended to asymmetric flow. The results are obtained in closed formulae and include stagnation streamline, location of the stagnation point, and typical fluid property variations. The results are compared with KAATTARI's method as well as with available experimental data.
An experiment is reported in which shock wave velocities, fluid pressures, magnetic fields and electric fields in Argon gas are measured in electromagnetic shock tube. It was observed that an ionizing shock wave which propates into a transverse magnetic field is partially reflected at the entrance of the magnetic field. The results of this experiment qualitively agreed with the theory proposed by KASAHARA, E. and MIIDA, Y.,
The nonlinear flexural vibration property of thin circular cylindrical shells with simply supported ends is analytically studied. The deflection mode is assumed so as to satisfy the continuity of the circumferential displacement in the large deflection theory and consists of the driven mode and its companion mode. The governing equations are derived by using HAMILTON'S principle. For the approximate solution of the nonlinear equation and its stability analysis, the method of averaging is used. The steady solution of the driven mode has the resonance curve of the softening type, and becomes unstable with the appearance of the companion mode at the region of the resonance. The values of the structural damping and the exciting force are effective for the stability of thesteady solution. In this unstable region the vibration of circumferentially traveling wave mode is stable. The present analytical results offer a satisfactory explanation to the available experimental observation.