On the assumption that the flow field near the stagnation point in the cylindrical shock layer is incompressible, inviscid and having a constant conductivity, the standoff distance of detached shock wave ahead of two-dimensional blunt bodies in the hypersonic flow under the influence of magnetic field is analyzed. Using a conical electromagnetic shock tube of 90m/mφ, detachment distances in front of two dimensional models as well as an axially symmetric model are measured with a rotating mirror camera and condenser banks to make magnetic field. Comparison is made concerning to the relation of nondimensional distance Δ/ΔNM to the value of Q at the stagnation point or Q*. Experimental values of Δ/ΔNM show rather good agreement with the theoretical results in the two dimensional case as well as the axially symmetric case.
In measuring high subsonic internal flows which are observed in high speed turbomachines such as transonic or supersonic compressors, authors planned to use a cylindrical probe which was supported at both ends, and got satisfactory results in the case of zero inclination angle. Furthermore, the inclination characteristics of this probe were investigated experimentally and it was revealed that the yaw angle of flow could be easily obtained independently of both Mach number M∞ and inclination angle α. It was also revealed that the flow component normal to the axis of the probe (total pressure P0, Mach number M∞) could be obtained with a fair accuracy from the characteristics of zero inclination angle within the range of not too large inclination angles (about ±15 degrees).