Transonic Flow With a Detached Bow Wave Past a Wedge Between Two Parallel Plane Walls

In the present paper the two-dimensional transonic flow with a detached bow wave past a doubly symmetrical double-wedge section placed midway between two parallel walls is investigated. The subsonic flow field oyer the front half of the profile is determined by applying the relaxation technique to the transonic perturbation equation in the hodograph plane. The method of characteristics is adopted for the supersonic flow over the rear half. Detailed computation has been carried out for three values of the ratio of the chord length to the tunnel width, assuming the value of the transonic parameter to be 0.921 in every case. Of the results, the following may be noted. When the tunnel width is gradually decreased, the bow wave moves forward and the pressure coefficients over the profile increase uniformly. However, a definite limit for the reduction of the tunnel width to maintain steady flow of a given (supersonic) Mach Number seems to exist. I t is not clear what happens exceeding this limit. The distance between the bow wave and the profile is comparatively small even in this limiting stage.